US3869101A - Infantry missile for combat against ground targets - Google Patents

Infantry missile for combat against ground targets Download PDF

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Publication number
US3869101A
US3869101A US358079A US35807973A US3869101A US 3869101 A US3869101 A US 3869101A US 358079 A US358079 A US 358079A US 35807973 A US35807973 A US 35807973A US 3869101 A US3869101 A US 3869101A
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US
United States
Prior art keywords
missile
trim
launching
forwardly
flight
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
US358079A
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English (en)
Inventor
Werner Schnabele
Georg Knoche
Fritz Zeyher
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm 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.)
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Publication date
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Publication of US3869101A publication Critical patent/US3869101A/en
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Expired - Lifetime legal-status Critical Current

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    • 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
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements

Definitions

  • ABSTRACT Infantry missile for combat against ground targets.
  • a missile which is to have an essentially flat trajectory, there is provided a smooth cylindrical body portion and associated therewith a forwardly sloped surface which during flight will cause the missile to assume a' trim angle capable of guiding it in a substantially horizontal flight path.
  • said forwardly sloping surface is at the forward end of a forwardly projecting horn-like detonator, in another embodiment the forwardly sloping surface is at the end of the otherwise cylindrical body part and in a still further embodiment said surface is on the lower side of the missile body as diverging upwardly flared surfaces.
  • means are also provided for guiding it from the launching tube in an attitude whereby its central longitudinal axis is already at the desired trim angle with the central longitudinal axis of the launching tube.
  • Such missiles may be constructed symmetrically with respect to rotation and may be stabilized on their path of flight by a rotational movement about their longitudinal axis.
  • wing-stabilized and nonrotating missiles are known, as for example described in the Oerlikon-Taschenbuch, Zurich-Oerlikon 1956, Page 134 and the following and Page 151 and the following.
  • German Auslegeschrift No. 1,094,159 discloses a missile which is aerodynamically stabilized by an annular wing and rotates about its longitudinal axis, on
  • German Patent No. 931,267 to mount at the head of a rotationally stabilized missile an interference surface which can intermittently be extended from the missile body.
  • a desired, including rectilinear, flight path can be obtained.
  • a constant rolling frequency of the missile is absolutely necessary because the extending frequency of the interference surface is coupled with it.
  • inaccuracies in the rolling frequency again cause deviations of the missile from its nominal flight path.
  • the control of the interference surface itself particularly after a long period of storage of the missile is a possible source of trouble.
  • a missile is known from Austrian Patent No. 57,039 which'has at its front part extendable stabilizing surfaces which also serve for straightening the flight path.
  • this device due to the required extending mechanism, is mechanically expensive and also after a long period of storage the missile may no longer be fully operative.
  • the purpose of the invention is to construct a simple and at the same time sturdy infantry missile for combat with ground targets in such a manner with respect to its shape and operation that it cannot be deflected by aerodynamic interference forces from a straight, preferably rectilinear, path of flight. Furthermore such a missile should be easy to handle and continue operative even after a long period of storage.
  • This purpose is attained according to the invention by providing a missile body which is symmetrical with respect to rotation, the rear part of which is constructed as a cylinder or cone jacket in order to achieve a path of flight which is free of spiral movements and is aerodynamically stable and by providing fixed trim means for achieving a straight, preferably rectilinear path of flight.
  • the basic form which is symmetrical with respect to rotation permits a recognizably simple manufacturing procedure for the missile.
  • struts or stabilizing wings rough handling of same is also permissible Without danger of damage.
  • storage is simplified in that it is now easy to stack the missiles.
  • the flight characteristics of the missle are improved compared with those of the known missiles because pressure differences which occur on the periphery of the missile body, which is symmetrical with respect to rotation during the flight, due to a lack of a point of application, cannot result in rolling or lateral flight path.
  • the trim means fixed tothe missile always maintains the desired fixed reference position required for obtaining a straight
  • the trim means is constructed as a sloped forward end closure of a horn-like extension of the missile which horn-like extension extends forwardly in direction of z the longitudinal axis of the missile.
  • the horn-like, in most cases an ignition device carrying, extension and sloped end can be manufactured easily with the highest precision in normal construction of the missile.
  • the trim moments which must thereby be produced are sufficiently great to achieve a straight justment, at targets which are located at varying distances.
  • the trim means is constructed as a forward sloped end for the frontpart of the missile body.
  • the stable rolling position of the missile which has been confirmed by the tests can according to a further embodiment of the invention be further maintained in thatthe missile has in at least a portion of the lower missile body keelmeans aligned in direction of the longitudinal axis.
  • This principle of stabilization of rolling position is already known in other fields, for example, in aircraft construction in the V-position of aircraft wings.
  • the keel means may of course itself be constructed as a trim surface.
  • the trim means affixed to the missile has the effect that after the launching from a launching device the missile is adjusted by aerodynamic moments which engage the trim means after a certain time of flight to a trim anglevin'relation to the tangent to its flight path.
  • the missile is guided within the launching'device itself at an angle with respect to the longitudinal nd embodiment of the invention
  • FIGS is a side view of said second embodiment
  • FIG. 4 is a fragmentary side view of a missile according to a third embodiment of the invention.
  • FIG. 5 is a partial cross-sectionalside view of the missile according to'the first exemplary embodiment during the launching from a launching device. 1
  • a missile I having a missile body which is symmetrical with respect to rotation is aerodynamically stabilized by a cylindrical jacket 2.
  • the front end of the missile 1 includes a 'cylindrically shaped horn-like extension 4 which is positioned symmetrically to its longitudinal axis 3, which contains a not-illustrated impact detonator and which is closed in front by a sloped trim surface 5.
  • aerodynamic forces will act onto this trim surface 5, which forces position the missile at the trim angle a with respect to the path of flight indicated by the arrow 6 in FIG. 1.
  • the angle 7, which the plane of the trim surface 5 defines, is so chosen with respect to the longitudinal axis 3 of the missile, that the path of flight of the missile is rectilinear within the projected range so that one sharpshooter can effectively aim for different distances without sight adjustment.
  • the front end of the missile 1 can be sloped and serve as trim surface 5.
  • the hornlike extension 4 does not need to be sloped in this case and may be rounded off or as illustrated closed off rectangularly.
  • trim surface is set forth above only as examples; other forms are, of course, possible and will be apparent to a man skilled in the art and working in this field.
  • the slider 9 has at its upper end an extension 11 which grips around the missile at its rear in the area of the cylinder jacket 2. This causes the cylinder jacket to be urged in its lower part against the launching tube 8.
  • the slider 10 which in its thickness equals the extension 11 is mounted in the front zone of the missile 1 so that the forward part of the missile is urged against the upper wall of the I launching tube 8.
  • the slider 10 is expelled from the launching tube and the missile l is already at the trim angle a with respect to its path of flight 6.
  • a nonrotationalinfantry missile launchable from a launching device primarily for combat against ground targets, comprising:
  • a cylindrical body the rear part of said body comprising means for achieving an aerodynamically stable flight position without missile rotation, such means defining a hollow cylindrical jacket;
  • V 2 The apparatus of claim 1, in which said lift producing trim means is a forwardly facing but sloped planar face centered on the central axis of the missile and arranged for lifting the forward end of the missile to a trim angle with respect to the path of flight.
  • trim means comprises a sloped front end closure face on said fixed extension.
  • trim means comprises a sloped closure face defining the front of said cylindrical body and from which said extension forwardly extends.
  • the apparatus of claim 1 including keel means formed in a lower part of said cylindrical body and extending substantially parallel to the longitudinal axis of said missile.
  • said hollow cylindrical jacket has an open rear end, and including a substantially forwardly facing linear profile closing the front of said body outward of said forward extension and being angled somewhat from a radial plane of the missile, said lift producing trim face being sloped downwardly during missile flight, said trim face having a central portion at least close to the missile longitudinal axis, said face being disposed at least near the front of the missile and ahead of said jacket.
  • trim face defines said linear profile, said trim face being somewhat downwardly facing but predominately forwardly facing and extending the full cross section of said body outside the periphery of said forward extension to provide said body with a skewed forward end.
  • the launching devicev comprises a launching tube, and including holding means slidable axially within the launching tube and releaseably bearing on the missile body when in said I launching tube for holding said missile body with its longitudinal axis inclined at an angle a to the longitudinal axis of the launching tube and with the forward end of said missile body thus elevated in the launching tube during launching, said holding means being adapted to fall away from said missile body when leaving the launching tube, said trim means comprising a surface oriented to maintain the missile axis forwardly elevated at a trim angle to the missile flight path after launching, said angle a being substantially equal to said trim angle whereby said missile is propelled from said launching tube already at said trim angle with respect to its flight path.
  • said holding means comprises spaced rear and front sliders
  • said rear slider comprising a transverse member spanning the interior cross section of the launching tube and having a forwardly and upwardly sloped front face abutting the rear end of said jacket, said rear slider having at its upper end a forward extension which grips around the rear area of said jacket for urging the lower portion of such jacket against the bottom peripheral wall of the launching tube, said front slider being normally disposed between the bottom peripheral wall of the launching tube and a forward portion of the missile body and corresponding in thickness to said extension of said rear slider so as to urge the forward part of said missile. body against the upper peripheral wall of the launching tube.
  • a method of launching a nonrotational missile from a launching device for achieving a rectilinear path of flight comprising;

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US358079A 1972-05-10 1973-05-07 Infantry missile for combat against ground targets Expired - Lifetime US3869101A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19722222785 DE2222785A1 (de) 1972-05-10 1972-05-10 Infanteriegeschoss zur bekaempfung von erdzielen

Publications (1)

Publication Number Publication Date
US3869101A true US3869101A (en) 1975-03-04

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ID=5844536

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US358079A Expired - Lifetime US3869101A (en) 1972-05-10 1973-05-07 Infantry missile for combat against ground targets

Country Status (6)

Country Link
US (1) US3869101A (enrdf_load_stackoverflow)
JP (1) JPS4922799A (enrdf_load_stackoverflow)
DE (1) DE2222785A1 (enrdf_load_stackoverflow)
FR (1) FR2183697B1 (enrdf_load_stackoverflow)
GB (1) GB1422404A (enrdf_load_stackoverflow)
IT (1) IT989207B (enrdf_load_stackoverflow)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4228973A (en) * 1974-12-05 1980-10-21 Messerschmitt-Bolkow-Blohm Gmbh Infantry projectile
US4374577A (en) * 1976-01-14 1983-02-22 The United States Of America As Represented By The Secretary Of The Navy Adapter assembly for flat trajectory flight
US4389028A (en) * 1976-01-14 1983-06-21 The United States Of America As Represented By The Secretary Of The Navy Flat trajectory projectile
WO1997007379A2 (en) 1995-08-17 1997-02-27 State Of Israel, Ministry Of Defense Rafael, Armament Development Authority Asymmetric penetration warhead
US6012393A (en) * 1995-08-17 2000-01-11 State Of Israel-Ministry Of Defense, Rafael-Armamient Dieve Asymmetric penetration warhead

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5839396B2 (ja) * 1978-08-25 1983-08-30 株式会社日立製作所 ガスレ−ザ発生装置
JP2716833B2 (ja) * 1990-01-31 1998-02-18 三菱重工業株式会社 ガスレーザ管
DE102005043474B4 (de) * 2005-09-13 2011-04-07 Deutsch-Französisches Forschungsinstitut Saint-Louis, Saint-Louis Vorrichtung zum Steuern eines Geschosses

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1459198A (en) * 1921-05-02 1923-06-19 Leonid A Dunajeff Projectile
US1896515A (en) * 1931-03-26 1933-02-07 Otto V Huffman Ammunition
US3086467A (en) * 1959-05-15 1963-04-23 John J Gallagher Gas operated extendible probe for ballistic model
US3132587A (en) * 1962-05-14 1964-05-12 Frank J Fuller Projectile
US3401637A (en) * 1966-09-28 1968-09-17 Madison H. Briscoe Broadside bullet

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1459198A (en) * 1921-05-02 1923-06-19 Leonid A Dunajeff Projectile
US1896515A (en) * 1931-03-26 1933-02-07 Otto V Huffman Ammunition
US3086467A (en) * 1959-05-15 1963-04-23 John J Gallagher Gas operated extendible probe for ballistic model
US3132587A (en) * 1962-05-14 1964-05-12 Frank J Fuller Projectile
US3401637A (en) * 1966-09-28 1968-09-17 Madison H. Briscoe Broadside bullet

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4228973A (en) * 1974-12-05 1980-10-21 Messerschmitt-Bolkow-Blohm Gmbh Infantry projectile
US4374577A (en) * 1976-01-14 1983-02-22 The United States Of America As Represented By The Secretary Of The Navy Adapter assembly for flat trajectory flight
US4389028A (en) * 1976-01-14 1983-06-21 The United States Of America As Represented By The Secretary Of The Navy Flat trajectory projectile
WO1997007379A2 (en) 1995-08-17 1997-02-27 State Of Israel, Ministry Of Defense Rafael, Armament Development Authority Asymmetric penetration warhead
WO1997007379A3 (en) * 1995-08-17 1997-05-22 Israel State Asymmetric penetration warhead
US6012393A (en) * 1995-08-17 2000-01-11 State Of Israel-Ministry Of Defense, Rafael-Armamient Dieve Asymmetric penetration warhead

Also Published As

Publication number Publication date
FR2183697A1 (enrdf_load_stackoverflow) 1973-12-21
GB1422404A (en) 1976-01-28
DE2222785A1 (de) 1973-11-22
IT989207B (it) 1975-05-20
FR2183697B1 (enrdf_load_stackoverflow) 1976-09-10
JPS4922799A (enrdf_load_stackoverflow) 1974-02-28

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