US3747533A - Short trajectory missile - Google Patents

Short trajectory missile Download PDF

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Publication number
US3747533A
US3747533A US00201521A US3747533DA US3747533A US 3747533 A US3747533 A US 3747533A US 00201521 A US00201521 A US 00201521A US 3747533D A US3747533D A US 3747533DA US 3747533 A US3747533 A US 3747533A
Authority
US
United States
Prior art keywords
missile
head
hollow space
forward end
axial channel
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
US00201521A
Other languages
English (en)
Inventor
R Rossmann
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.)
Rheinmetall Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle 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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Application granted granted Critical
Publication of US3747533A publication Critical patent/US3747533A/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
    • 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
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/52—Nose cones

Definitions

  • the present invention relates to a short trajectory missile with a missile body and a missile head which separates from the body during the flight of the missile.
  • a missile of this kind should have the same external ballistic characteristics for practice purposes in the range or area of utilization as the or actual type corresponding thereto.
  • means or agents should become effective to alter the ballistic characteristics of the missile in such a way that the flight trajectory will be considerably reduced in comparison with that of the effective or actual missile.
  • the missile head is held by balls which are introduced into the missile head, into which a groove of the missile body projects and is held by a pin.
  • a safety bolt is sheared off and the pin is thrown backwards, so that the balls become free.
  • these balls are pressed outwardly into the aforementioned groove by centrifugal force.
  • the balls fall out of the groove in the braking area, and the missile head is thrown forward by a spring, as a result of which the missile head and missile body rapidly loose speed and fall to the ground.
  • a disadvantage with this missile is that a large number of components are required for the separation of the missile head, as a result of which the manufacture of the missile requires considerable expenditure in time and money.
  • a short trajectory missile comprising a missile body and a missile head capable of separating during the flight of the missile, wherein a part of the missile head comprises material capable of melting due to the friction of air resistance.
  • a front end of the missile head consists of a material capable of melting as a result of the friction of air resistance, and the missile head has a hollow space, so that after the melting of the aforementioned front end, the missile head bursts as a result of a momentary increase in air pressure into the hollow space and is separated from the missile body.
  • the missile has a very simple construction, whereby the flight range can be determined by a corresponding dimensioning of the missile head.
  • the exter- 'nal ballistic characteristics of the missile can be matched to those of the effective or actual missle by weight and shaping of the missile body and missile head.
  • FIG. ll shows a longitudinal section through the short trajectory missile
  • FIG. 2 shows the short trajectory missile of FIG. l but without protective hood and plastics sheath during flight in the area of use;
  • FIG. 3 shows the short trajectory missile of FIG. 2, without the separated missile head during flight in the braking zone.
  • FIG. 1 shows a missile body I provided at its front end with an axially drilled channel 2 into which extend four radially drilled holes 3, which are mutually perpendicular to each other.
  • the missile body ll has an annular front surface 4, which is engaged by annular ridge 6 of a missle head 5, the missile head 5 projecting into the channel 2.
  • the missile head 5 tapers to a front end 8 and has an interior hollow space 7 opening rearwardly into channel 2.
  • the missile head 5 is thus hollow and is made from a material capable of melting as a result of the friction of air resistance, in this case plastic material.
  • the missile body I is surrounded by a plastic sheath 9, which at its rear end has a guiding and sealing band 10.
  • a protective hood Ill surrounds the missile head 5 and the front end of missile body l and is secured in an annular groove 112 of the plastic sheath 9.
  • FIG. 3 shows the missile while in the braking zone whereby the unfavourable flow ratios are represented by flow lines S and 8,.
  • the protective hood 11 and plastic sheath 9 are separated from the missile body by centrifugal force.
  • the missile, including the missile head 5, now posses a favourable, low resistance external shape, creating flow lines S, and S (see FIG. 2).
  • the front end 8 of the missile head undergoes, as a result of the friction of air resistance, an increase in temperature, which, for example, at a missile velocity of 1,300/m/s is about 850 C and causes the missile head to melt.
  • the wall thickness of the hollow missile head 5 is dimensioned so that the possibility of melting through in the area of utilization :is avoided, that is to say, that the optimum missile shape is maintained in the area of utilization.
  • the four radial drillings 3 are arranged mutually perpendicular to each other, or in other words, they are arranged symmetrically in relation to a plane running through the longitudinal centre line A of the missile.
  • the stability of the missile body is additionally disturbed in the braking zone. A resultant movement similar to a pendulum movement occurs, so that the flight trajectory is even further reduced.
  • a short trajectory training missile comprising: a missile body; a missile head separably attached to the forward end of said missile body; said attached missile body and missile head having an exterior shape to produce external ballistic characteristics within the range of desired utilization identical to those of a corresponding actual missile; said missile having means for causing said missile head to separate from said missile body upon passage of said missile from said range of utilization, thereby substantially altering the ballistic characteristics of said missile, and for imparting a rapid braking of the trajectory of said missile; said means comprising a hollow space on the interior of said missile head, and a forward end of said missile head closing said hollow space, said forward end being formed of a material capable of being melted through by the friction of air resistance upon the passage of said missile from said range of utilization, whereby said hollow space is subjected to an instantaneous air pressure increase, and said missile head being formed of a material capable of bursting under the force of such interior air pressure increase.
  • a missile is claimed in claim 1, further comprising an axial channel extending into said missile body from the forward end thereof, said missile head extending into said axial channel, said hollow space communicating with said axial channel and at least one radial hole extending outwardly through said missile body from said axial channel to the exterior of said missile, whereby when said forward end of said missile head melts, air passes through said hollow space, inJo said axial channel, and outwardly through said at least one radial hole, thereby creating increased rapid braking of the trajectory of said missile.
  • a missile as claimed in claim 2, wherein said at least one radial hole comprises a plurality of radial holes symmetrically spaced around said missile body.
  • a missile as claimed in claim 2, wherein said at least one radial hole. comprises a plurality of radial holes asymmetrically spaced around said missile body.
  • a missile as claimed in claim 2, wherein said at least one radial hole comprises four radial holes spaced around said missile body.

Landscapes

  • 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)
  • Braking Arrangements (AREA)
US00201521A 1970-12-08 1971-11-23 Short trajectory missile Expired - Lifetime US3747533A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1832670A CH532240A (de) 1970-12-08 1970-12-08 Kurzbahngeschoss

Publications (1)

Publication Number Publication Date
US3747533A true US3747533A (en) 1973-07-24

Family

ID=4432163

Family Applications (1)

Application Number Title Priority Date Filing Date
US00201521A Expired - Lifetime US3747533A (en) 1970-12-08 1971-11-23 Short trajectory missile

Country Status (5)

Country Link
US (1) US3747533A (fr)
BE (1) BE775798A (fr)
CH (1) CH532240A (fr)
FR (1) FR2114879A5 (fr)
GB (1) GB1319923A (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3948184A (en) * 1972-10-10 1976-04-06 Etat Francais Sub-calibre projectile shells
US4128060A (en) * 1976-04-13 1978-12-05 Dynamit Nobel Aktiengesellschaft Short-range projectile for practice ammunition
US4136616A (en) * 1975-08-09 1979-01-30 Schirnecker Hans Ludwig Cartridge for hand and shoulder firearms
US4140061A (en) * 1977-06-06 1979-02-20 The United States Of America As Represented By The Secretary Of The Army Short-range discarding-sabot training practice round and self-destruct subprojectile therefor
US4142467A (en) * 1976-07-09 1979-03-06 Dynamit Nobel Aktiengesellschaft Projectile with sabot
EP0090888A1 (fr) * 1982-03-05 1983-10-12 The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Projectile d'entraînement à sabot séparable
EP0123978A2 (fr) * 1983-04-23 1984-11-07 Rheinmetall GmbH Coiffe pour projectile à noyau perforant
US4572077A (en) * 1981-09-24 1986-02-25 Societe Francaise De Munitions Projectile for hand and shoulder weapons and a cartridge fitted with said projectile
US5001986A (en) * 1989-03-03 1991-03-26 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Short-range projectile containing means for producing a short flight path
US5003886A (en) * 1986-03-19 1991-04-02 Rheinmetall Gmbh Projectile for combatting actively and passively recting armor
US20110107937A1 (en) * 2006-10-19 2011-05-12 David Thompson Special purpose small arms ammunition
US9157713B1 (en) 2013-03-15 2015-10-13 Vista Outdoor Operations Llc Limited range rifle projectile

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2551196B1 (fr) * 1976-06-02 1986-06-06 France Etat Armement Projectile d'exercice a portee reduite pour un champ de tir a gabarit reduit
DE2756420C2 (de) * 1977-12-17 1985-02-07 Rheinmetall GmbH, 4000 Düsseldorf Geschoß mit selbsttätiger Zerlegerwirkung
BE882272A (fr) * 1980-03-18 1980-09-18 Herstal Sa Munition d'entrainement
FR2547407B1 (fr) * 1983-06-08 1990-09-28 Mecanique Ste Nle Et Projectile d'exercice pour artillerie a freinage de trajectoire et marquage d'impact
DE8807701U1 (de) * 1988-06-14 1989-10-12 Diehl GmbH & Co, 8500 Nürnberg Übungsgeschoß

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2987999A (en) * 1959-02-12 1961-06-13 Jr Ralph O Robinson Protective cover
US3106162A (en) * 1959-05-08 1963-10-08 John P Hagerty Nose cooling means for missiles
US3496869A (en) * 1967-07-28 1970-02-24 Oerlikon Buehrle Holding Ag Sabot projectile
US3580179A (en) * 1967-09-06 1971-05-25 Dynamit Nobel Ag Ammunition for target practice or other short-range purposes

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2987999A (en) * 1959-02-12 1961-06-13 Jr Ralph O Robinson Protective cover
US3106162A (en) * 1959-05-08 1963-10-08 John P Hagerty Nose cooling means for missiles
US3496869A (en) * 1967-07-28 1970-02-24 Oerlikon Buehrle Holding Ag Sabot projectile
US3580179A (en) * 1967-09-06 1971-05-25 Dynamit Nobel Ag Ammunition for target practice or other short-range purposes

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3948184A (en) * 1972-10-10 1976-04-06 Etat Francais Sub-calibre projectile shells
US4136616A (en) * 1975-08-09 1979-01-30 Schirnecker Hans Ludwig Cartridge for hand and shoulder firearms
US4128060A (en) * 1976-04-13 1978-12-05 Dynamit Nobel Aktiengesellschaft Short-range projectile for practice ammunition
US4142467A (en) * 1976-07-09 1979-03-06 Dynamit Nobel Aktiengesellschaft Projectile with sabot
US4140061A (en) * 1977-06-06 1979-02-20 The United States Of America As Represented By The Secretary Of The Army Short-range discarding-sabot training practice round and self-destruct subprojectile therefor
US4572077A (en) * 1981-09-24 1986-02-25 Societe Francaise De Munitions Projectile for hand and shoulder weapons and a cartridge fitted with said projectile
EP0090888A1 (fr) * 1982-03-05 1983-10-12 The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Projectile d'entraînement à sabot séparable
EP0123978A2 (fr) * 1983-04-23 1984-11-07 Rheinmetall GmbH Coiffe pour projectile à noyau perforant
EP0123978A3 (en) * 1983-04-23 1985-05-15 Rheinmetall Gmbh Nose cap for a projectile with an armour-piercing core
US5003886A (en) * 1986-03-19 1991-04-02 Rheinmetall Gmbh Projectile for combatting actively and passively recting armor
US5001986A (en) * 1989-03-03 1991-03-26 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Short-range projectile containing means for producing a short flight path
US20110107937A1 (en) * 2006-10-19 2011-05-12 David Thompson Special purpose small arms ammunition
US8176850B2 (en) * 2006-10-19 2012-05-15 Xtek Limited Special purpose small arms ammunition
US9157713B1 (en) 2013-03-15 2015-10-13 Vista Outdoor Operations Llc Limited range rifle projectile

Also Published As

Publication number Publication date
GB1319923A (en) 1973-06-13
DE2155467A1 (de) 1972-06-22
BE775798A (fr) 1972-03-16
DE2155467B2 (de) 1975-08-21
FR2114879A5 (fr) 1972-06-30
CH532240A (de) 1972-12-31

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