US3238875A - Rocket shell construction - Google Patents

Rocket shell construction Download PDF

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Publication number
US3238875A
US3238875A US275866A US27586663A US3238875A US 3238875 A US3238875 A US 3238875A US 275866 A US275866 A US 275866A US 27586663 A US27586663 A US 27586663A US 3238875 A US3238875 A US 3238875A
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US
United States
Prior art keywords
end portion
rear end
stabilizer fin
sleeve
body rear
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
US275866A
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English (en)
Inventor
Hans K Stadler
Gawlick Heinz
Stahlmann Rudolf
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.)
Dynamit Nobel AG
Original Assignee
Dynamit Nobel AG
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 Dynamit Nobel AG filed Critical Dynamit Nobel AG
Application granted granted Critical
Publication of US3238875A publication Critical patent/US3238875A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/08—Ordnance projectiles or missiles, e.g. shells
    • F42B30/10—Mortar projectiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins

Definitions

  • stabilization fins In the construction of rocket shells, a problem exists with respect to the providing of stabilization fins.
  • the stabilization fins must fulfill the required aerodynamic requirements and at the same time should be of reasonable cost, and of suitable strength and resistance to withstand operating conditions. This problem is of particular significance which it is desired to use stabilizing fins of plastic material.
  • the principal object of the invention is to provide a rocket shell construction particularly as it relates to the stabilizing fins and the mounting thereof, which is of a nature to meet the condition referred to above.
  • a rocket shell comprises an elongated. body having a forward end portion and a rear end portion, a closure for the rear end portion, a stabilizer fin assembly mounted on the rear end portion, and means securing the stabilizer fin suspension on the body rear end portion.
  • the stabilizer fin assembly includes a plurality of stabilizer fins joined at their base to a stabilizer fin sleeve, and the stabilizer fins extend radially outwardly from the sleeve.
  • the sleeve is positioned about the body rear end portion, and the means interconnecting the stabilizer fin assembly and the body rear end portion comprises key means disposed circumferentially about the body rear end portion and which interconnects the stabilizer fin assembly sleeve and the body rear end portion in a manner to fixedly secure the stabilizer fin assembly on the body rear end. portion to prevent axial and rotational movement of the stabilizer fin assembly on the body rear end portion.
  • the construction provided by the invention has particular application in respect to training rockets, and hence, in rocket shell utilizing the construction of the invention there can be radial openings through body portion forward of the stabilizer fin assembly and adjacent thereto.
  • the key means interconnecting the stabilizer fin assembly and the body rear end portion can be a spline and integral with either the sleeve or the body rear end portion, the spline extending circumferentially about the part that it is integral with.
  • the part not provided with a spline is then provided with a circumferentially extending groove for receipt of the spline.
  • the spline construction the spline fits tightly in the groove provided there-for and secures the stabilizer fin assembly in a fixed position so that it is axially fixed and is restrained against rotation about the body portion of the shell.
  • the stabilizer fin assembly is positioned on the shell body rear end portion by forcing the pin assembly and shell together by moving these parts axially with respect to each other so that the part bearing the groove passes over the spline to the extent that the spline and groove come to opposed relation, whereupon the spline snaps into the groove.
  • One of the parts, either the stabilizer fin assembly or the shell rear end portion, is of material which is resiliently yieldable to the extent that the parts can be assembled in the manner described.
  • the spline is integral with the rear end portion of the shell body.
  • An alternative manner of mounting the stabilizer fin assembly on the shell by a key interconnection is to provide each, the stabilizer fin assembly and the body rear end portion, with a circumferentially extending groove, these two grooves being in communication with the stabilizer fin assembly in the normal mounted position.
  • a split ring then serves as the key interconnecting means, the split ring being positioned in the grooves.
  • FIG. 1 is an elevational view of a portion of a rocket shell according to the invention
  • FIG. 2 is the same as FIG. 1, except that a part of the rocket shell is shown in cross-section, along line 11-11 in FIG. 1;
  • FIG. 3 is a plan view, in cross-section, taken along line IIIIII in FIG. 1;
  • FIG. 4 is a view of a alternative construction and corresponds with FIG. 2;
  • FIG. 5 is a plan, cross-section, view taken along line VV in FIG. 4.
  • the rocket shell comprises a body having a forward end portion 1 and a rear end portion 11.
  • a stabilizer fin assembly is made up of the stabilizer fins 6 which are secured at their base to the sleeve 7. Forward of the stabilizer fin assembly there are radially extending openings 12, and a cup 3 having an exhaust opening 4 is mounted on the rear edge portion of the shell body. This cup is fixedly secured in place by any suitable means such as a tight threaded connection.
  • the mounting of the stabilizer fin assembly on the shell body rear end portion 11 can be best seen in FIG. 2 and FIG. 3.
  • the body rear end portion is provided with integrally formed radially outwardly extending splines 8; the sleeve 7 of the stabilizer fin assembly is provided with circumferentially extending grooves 8 which receive the splines 9.
  • the splines 9 fit tightly in the grooves 8 so that the stabilizer fin assembly is prevented from moving axially with respect to the body portion, and, further, is prevented from rotating on the body portion.
  • Either the stabilizer fin assembly or the rear end. portion of the shell is of such material that it is resiliently yieldable so that the stabilizer fin assembly can be positioned on the rocket shell by forcing the stabilizer fin assembly axially over the splines 9.
  • the inner forward circumferential edge of the stabilizer fin assembly sleeve 7 is provided with a guide surface 10 so that upon sliding the stabilizer fin assembly shell 7 over the rear edge portion of the rocket shell to the extent that the forward portion of the shell 7 engages the rearrnost spline 8, the shell presents an inclined surface to the engaged spline, whereupon, when force is applied, the shell can be made to rise up over the spline. The shell can then be forced on to the extent that the slots 8 are in opposed relation to the splines 9, and the splines 9 then snap into the slots 8.
  • the key means interconnecting the stabilizer fin assembly and the rocket shell comprises split rings.
  • each of the stabilizer fin assembly sleeve 7 and the body rear end portion 1 1 are provided with grooves 14, and the body rear end portion 11 is provided with grooves 15. With the stabilizer fin assembly in its normal position mounted on the rocket shell, these grooves are in opposed and communicating relation.
  • a split ring .16 is disposed in each pair of opposed, communicating grooves and serves to fixedly position the stabilizer fin assembly on the body rear end portion in the manner previously described.
  • the split ring is positioned in the grooves on the body rear end portion 11 and is compressed to reduce its diameter, as is permitted by the split in the split ring, and the stabilizer fin assembly shell 7 is then slid over the split rings to the extent that the grooves 14 in the shell 7 come to opposed relation with the split rings, whereupon the split rings snap into place bridging the grooves in the shell rear end portion and in the stabilizer fin sleeve 7, providing a key connection between these parts.
  • the stabilizer fin assembly can be, and preferably is, a one piece structure formed of non-combustible plastic.
  • the shell or the shell rear end portion can be of similar material.
  • the interconnecting key means for the stabilizer fin assembly and shell rear end portion is a spline integral with one of these parts, the spline can be of the material of the part with which it is integral.
  • the split ring can be of plastic or of a suitable metal.
  • a rocket shell comprising:
  • a stabilizer fin assembly mounted on the rear end portion, said stabilizer fin assembly including a plurality of stabilizer fins joined at their base to a stabilizer fin sleeve and extending radially outwardly from the stabilizer fin sleeve;
  • said key means comprising a spline integral with one of said stabilizer fin sleeve and the body rear end portion, the other of said stabilizer fin sleeve and body end portion having a circumferentially extending slot receiving the spline and providing said interconnection of the stabilizer fin assembly sleeve and the body rear end portion;
  • At least one of said stabilizer fin sleeve and said body rear end portion being resiliently yieldable permitting mounting of the stabilizer fin sleeve on the body rear end portion with said spline engaged as aforesaid by forcing the stabilizer fin sleeve axially of the body rear end portion to the extent that the spline becomes engaged in the circumferential slot as aforesaid.
  • a rocket shell according to claim 1 said rocket shell being a training shell having means defining radially extending openings through the rocket shell, forward of the stabilizer fin assembly and adjacent thereto.
  • a rocket shell according to claim 1 said closure for the rocket shell rear end portion being a cup, said cup receiving a rear edge portion of the body member and being fixedly mounted on the body member.
  • a rocket shell according to claim 1 the said spline being integral with the rear end portion.
  • a rocket shell according to claim 1 the stabilizer fin assembly being formed of non-combustible plastic, the stabilizer fin being integral with the stabilizer fin sleeve.
  • a rocket shell comprising:
  • a stabilizer fin assembly mounted on the rear end portion, said stabilizer fin assembly including a plurality of stabilizer fins joined at their base to a stabilizer fin sleeve and extending radially outwardly from the stabilizer fin sleeve;
  • said key means comprising split rings compressed in said slots
  • At least one of said stabilizer fin sleeve and said body rear end portion being resiliently yieldable permitting mounting of the stabilizer fin sleeve on the body rear end portion with said spline engaged as aforesaid by forcing the stabilizer fin sleeve axially of the body rear end portion to the extent that the spline becomes engaged in the circumferential slot as aforesaid.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
US275866A 1962-04-27 1963-04-26 Rocket shell construction Expired - Lifetime US3238875A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DED38785A DE1236376B (de) 1962-04-27 1962-04-27 Leitwerk fuer Raketen

Publications (1)

Publication Number Publication Date
US3238875A true US3238875A (en) 1966-03-08

Family

ID=7044332

Family Applications (1)

Application Number Title Priority Date Filing Date
US275866A Expired - Lifetime US3238875A (en) 1962-04-27 1963-04-26 Rocket shell construction

Country Status (6)

Country Link
US (1) US3238875A (de)
AT (1) AT246612B (de)
BE (1) BE625273A (de)
DE (1) DE1236376B (de)
GB (1) GB1024864A (de)
NL (1) NL285423A (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3640489A (en) * 1968-07-26 1972-02-08 Karl Jaeger Vertical takeoff and landing aircraft
US3765620A (en) * 1970-07-11 1973-10-16 Tampella Oy Ab Fin assembly for fin-stabilized projectiles, and a process for its manufacture
US5158509A (en) * 1990-12-14 1992-10-27 The United States Of America As Represented By The United States Department Of Energy Composite stabilizer unit
US5228855A (en) * 1992-03-31 1993-07-20 Ffe International Mortar training ammunition device having independently rotatable vent closure rings
US20050115220A1 (en) * 2003-12-01 2005-06-02 Shanker Mo Hydraulic rocket
US6978967B1 (en) * 2003-04-25 2005-12-27 The United States Of America As Represented By The Secretary Of The Army Space saving fin deployment system for munitions and missiles
WO2012031604A1 (de) * 2009-08-04 2012-03-15 Rheinmetall Waffe Munition Gmbh Mörsergranate

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2268575A (en) * 1992-07-09 1994-01-12 Secr Defence Tail fin unit

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1257126A (en) * 1917-12-24 1918-02-19 Eugene Schneider Explosive projectile.
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
FR1061958A (fr) * 1952-05-19 1954-04-16 Le Moulage De Prec Perfectionnements aux empennages
FR1077083A (fr) * 1953-03-20 1954-11-04 Soc Tech De Rech Ind Empennage pour projectiles
US2787481A (en) * 1952-08-20 1957-04-02 Hydrocarbon Research Inc Transition pipe coupling
US2886355A (en) * 1955-08-09 1959-05-12 Waldes Kohinoor Inc Coupled assemblies and coupling ring for use therein
US2890073A (en) * 1952-03-27 1959-06-09 Raymond W Thomas Separable joint for tubular members
US2899215A (en) * 1959-08-11 ardito
US2901973A (en) * 1953-12-10 1959-09-01 Donner Hans Otto Diaphragm means for subcalibre non-spinning projectiles
US3018547A (en) * 1952-07-30 1962-01-30 Babcock & Wilcox Co Method of making a pressure-tight mechanical joint for operation at elevated temperatures

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR530223A (fr) * 1921-01-27 1921-12-17 Perfectionnements apportés aux projectiles, en vue d'augmenter la longueur de leur trajectoire
FR1065756A (fr) * 1952-10-23 1954-05-31 Le Moulage De Prec Empennage perfectionné

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2899215A (en) * 1959-08-11 ardito
US1257126A (en) * 1917-12-24 1918-02-19 Eugene Schneider Explosive projectile.
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
US2890073A (en) * 1952-03-27 1959-06-09 Raymond W Thomas Separable joint for tubular members
FR1061958A (fr) * 1952-05-19 1954-04-16 Le Moulage De Prec Perfectionnements aux empennages
US3018547A (en) * 1952-07-30 1962-01-30 Babcock & Wilcox Co Method of making a pressure-tight mechanical joint for operation at elevated temperatures
US2787481A (en) * 1952-08-20 1957-04-02 Hydrocarbon Research Inc Transition pipe coupling
FR1077083A (fr) * 1953-03-20 1954-11-04 Soc Tech De Rech Ind Empennage pour projectiles
US2901973A (en) * 1953-12-10 1959-09-01 Donner Hans Otto Diaphragm means for subcalibre non-spinning projectiles
US2886355A (en) * 1955-08-09 1959-05-12 Waldes Kohinoor Inc Coupled assemblies and coupling ring for use therein

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3640489A (en) * 1968-07-26 1972-02-08 Karl Jaeger Vertical takeoff and landing aircraft
US3765620A (en) * 1970-07-11 1973-10-16 Tampella Oy Ab Fin assembly for fin-stabilized projectiles, and a process for its manufacture
US5158509A (en) * 1990-12-14 1992-10-27 The United States Of America As Represented By The United States Department Of Energy Composite stabilizer unit
US5228855A (en) * 1992-03-31 1993-07-20 Ffe International Mortar training ammunition device having independently rotatable vent closure rings
US6978967B1 (en) * 2003-04-25 2005-12-27 The United States Of America As Represented By The Secretary Of The Army Space saving fin deployment system for munitions and missiles
US20050115220A1 (en) * 2003-12-01 2005-06-02 Shanker Mo Hydraulic rocket
WO2012031604A1 (de) * 2009-08-04 2012-03-15 Rheinmetall Waffe Munition Gmbh Mörsergranate

Also Published As

Publication number Publication date
AT246612B (de) 1966-04-25
GB1024864A (en) 1966-04-06
NL285423A (de)
BE625273A (de)
DE1236376B (de) 1967-03-09

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