EP0068300B1 - Anordnung zur Kursausrichtung von in Flüssigkeiten bewegten Raketen - Google Patents

Anordnung zur Kursausrichtung von in Flüssigkeiten bewegten Raketen Download PDF

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Publication number
EP0068300B1
EP0068300B1 EP82105259A EP82105259A EP0068300B1 EP 0068300 B1 EP0068300 B1 EP 0068300B1 EP 82105259 A EP82105259 A EP 82105259A EP 82105259 A EP82105259 A EP 82105259A EP 0068300 B1 EP0068300 B1 EP 0068300B1
Authority
EP
European Patent Office
Prior art keywords
rocket
magnet
arrangement
liquid medium
course
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
Application number
EP82105259A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0068300A3 (en
EP0068300A2 (de
Inventor
Karl Dr. Wisseroth
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.)
BASF SE
Original Assignee
BASF SE
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 BASF SE filed Critical BASF SE
Publication of EP0068300A2 publication Critical patent/EP0068300A2/de
Publication of EP0068300A3 publication Critical patent/EP0068300A3/de
Application granted granted Critical
Publication of EP0068300B1 publication Critical patent/EP0068300B1/de
Expired 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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • E—FIXED CONSTRUCTIONS
    • E21—EARTH OR ROCK DRILLING; MINING
    • E21C—MINING OR QUARRYING
    • E21C37/00—Other methods or devices for dislodging with or without loading
    • E21C37/005—Other methods or devices for dislodging with or without loading by projectiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
    • F42B19/01—Steering control
    • F42B19/06—Directional control

Definitions

  • the invention relates to an arrangement for the horizontal course alignment of rockets moving in liquids.
  • Missiles launched in liquids - e.g. B. water - are used, for example, to bring explosives to solid materials to be shredded.
  • the explosive destruction of hard coal in a coal seam filled with liquid and in the process of being mined For this purpose, the rocket carrying the explosives is fed into the seam through a hole from above ground. After reaching the bottom of the mine, the rocket generally aligns itself automatically by regulating the center of gravity at an intended elevation angle, which predominantly corresponds to the horizontal or only slightly deviates from it. The azimuth angle, however, remains indefinite, so that after the propellant has been ignited, the rocket will move in any randomly set horizontal direction.
  • the task was therefore to develop an arrangement by means of which the direction of movement of rockets moving in liquids can also be adjusted with regard to their azimuthal orientation.
  • the object was achieved in that the rocket body is connected to a magnet and the rocket axis and the magnetic axis of the magnet form an azimuthal angle ⁇ , which determines the target direction of the rocket with respect to the geomagnetic meridian.
  • Fig. 1 the arrangement according to the invention for horizontal course alignment is shown schematically. It consists of the rocket body 1 to be moved and a bar magnet 2 attached to it on the outside or inside. This is fixed to the rocket body by screws or pins or other suitable fastening means in such a way that the rocket axis 3 and the axis 4 of the bar magnet 2 form an azimuthal angle a, which determines the direction of the missile with respect to the geomagnetic meridian 5 (FIG. 2).
  • the aligning force K is defined by the torque acting at the pivot point of the rocket body according to the mathematical relationship where a is the force arm and H is the earth's magnetic field strength, M is the magnetic moment of the bar magnet 2 and n is the azimuthal angle.
  • the geomagnetic field is relatively weak.
  • the required directional force K can, however, be achieved by suitable selection of the magnetic moment of the bar magnet.
  • the force K to be used serves to overcome both inertial forces and the moment of inertia correspond to the rocket to be oriented, where ⁇ is the angular acceleration, as well as the frictional forces that are already noticeable in a liquid.
  • the permanent magnets available have sufficiently high residual flux densities with which both the inertial forces and the frictional forces can be easily overcome. The friction forces even proved useful in one respect by supporting the swinging into the end position by strongly damping the rotary movement.
  • the bar magnet 2 can be connected to the rocket as additional ballast, as illustrated, for example, by FIG. 3.
  • an orientation of the elevation angle / l of the direction of the missile can be effected at the same time.
  • This combined measure means that practically every point P of a spherical reference space around the center of gravity of the rocket can be reached (FIG. 2).
  • Barium ferrites or cast magnets made of aluminum-nickel-cobalt alloy are particularly suitable as materials for the bar magnets.
  • a rocket 20 cm long and 3.5 cm in diameter has a propellant charge of 25 g of pressed black powder. It also carries a load of 250 g explosives. To stabilize the course, a sleeve tail of 10 cm length and 5 cm diameter is pushed coaxially over the missile body at the end of the missile, so that the sleeve end protrudes 5 cm beyond the nozzle opening. Below the rocket is a bar magnet of 50 g weight and a magnetic moment of 5 ⁇ 10 7 V ⁇ s ⁇ m, whose magnetic north-south axis is rotated 45 "against the rocket axis, so that the rockets after alignment pointed towards the northwest.
  • the complete rocket arrangement is introduced with a random directional orientation into a concentrated CaC1 2 solution (density 1.40 g / cm 3 ), which is under a pressure of 150 bar. After about 2 seconds the rocket has leveled off in the intended direction and points to the target location. The propellant charge is then ignited with an overpressure igniter delayed by 5 seconds. It then moves towards the destination at a stable course, where the explosive charge is detonated by a detonator.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mining & Mineral Resources (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Life Sciences & Earth Sciences (AREA)
  • Geochemistry & Mineralogy (AREA)
  • Geology (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Hard Magnetic Materials (AREA)
EP82105259A 1981-06-26 1982-06-16 Anordnung zur Kursausrichtung von in Flüssigkeiten bewegten Raketen Expired EP0068300B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3125108 1981-06-26
DE19813125108 DE3125108A1 (de) 1981-06-26 1981-06-26 "anordnung zur kursausrichtung von in fluessigkeiten bewegten raketen"

Publications (3)

Publication Number Publication Date
EP0068300A2 EP0068300A2 (de) 1983-01-05
EP0068300A3 EP0068300A3 (en) 1983-03-16
EP0068300B1 true EP0068300B1 (de) 1985-03-06

Family

ID=6135417

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82105259A Expired EP0068300B1 (de) 1981-06-26 1982-06-16 Anordnung zur Kursausrichtung von in Flüssigkeiten bewegten Raketen

Country Status (6)

Country Link
US (1) US4601251A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
EP (1) EP0068300B1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
AU (1) AU8534382A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (2) DE3125108A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
IN (1) IN155804B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
ZA (1) ZA824530B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8015922B2 (en) * 2009-03-07 2011-09-13 Lockheed Martin Corporation Control system for right circular cylinder bodies
CN110260714B (zh) * 2019-05-21 2020-07-10 中国人民解放军海军工程大学 制导弹药外弹道半实物仿真平台及方法

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US333008A (en) * 1885-12-22 Island
US1228364A (en) * 1916-10-18 1917-05-29 A J Macy Automatic pilot mechanism.
US1378740A (en) * 1917-07-30 1921-05-17 Walkup Samuel Thomas Autogubernator
US1410872A (en) * 1920-05-07 1922-03-28 Frederick W Baldwin Torpedo
FR581367A (fr) * 1924-05-07 1924-11-27 Dispositif pour la direction des torpilles
US2363363A (en) * 1940-08-30 1944-11-21 George A Rubissow Automatic system for controlling the direction of moving bodies
US2338322A (en) * 1942-02-28 1944-01-04 Antonio R Ferrer Torpedo
US2493788A (en) * 1942-09-29 1950-01-10 Joseph D Turlay Resilient support for the firing control mechanism of a marine mine
US2596120A (en) * 1949-10-13 1952-05-13 Thomas C Boyle Variable length torpedo head
US2937824A (en) * 1955-07-11 1960-05-24 Aerojet General Co Bi-medium rocket-torpedo missile
US3060854A (en) * 1959-12-21 1962-10-30 Perma Pier Inc Underwater rocket
US3134353A (en) * 1962-03-20 1964-05-26 Thiokol Chemical Corp Underwater propulsion system
DE3108425A1 (de) * 1981-03-06 1982-09-23 Basf Ag, 6700 Ludwigshafen Verfahren zur erschliessung sehr tief liegender kohlefloeze

Also Published As

Publication number Publication date
EP0068300A3 (en) 1983-03-16
US4601251A (en) 1986-07-22
EP0068300A2 (de) 1983-01-05
DE3262491D1 (en) 1985-04-11
IN155804B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1985-03-09
DE3125108A1 (de) 1983-01-13
ZA824530B (en) 1983-05-25
AU8534382A (en) 1983-01-06

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