EP0302766A1 - Steuerungsvorrichtung für die Scharfstellung einer Rakete oder ähnlichen beweglichen Gegenständen - Google Patents

Steuerungsvorrichtung für die Scharfstellung einer Rakete oder ähnlichen beweglichen Gegenständen Download PDF

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Publication number
EP0302766A1
EP0302766A1 EP88401669A EP88401669A EP0302766A1 EP 0302766 A1 EP0302766 A1 EP 0302766A1 EP 88401669 A EP88401669 A EP 88401669A EP 88401669 A EP88401669 A EP 88401669A EP 0302766 A1 EP0302766 A1 EP 0302766A1
Authority
EP
European Patent Office
Prior art keywords
parachute
cover
slide
machine
halyard
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.)
Withdrawn
Application number
EP88401669A
Other languages
English (en)
French (fr)
Inventor
Alain Maillochon
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.)
Safran Aerosystems SAS
Original Assignee
Aerazur SAS
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 Aerazur SAS filed Critical Aerazur SAS
Publication of EP0302766A1 publication Critical patent/EP0302766A1/de
Withdrawn legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42CAMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C14/00Mechanical fuzes characterised by the ammunition class or type
    • F42C14/06Mechanical fuzes characterised by the ammunition class or type for fall bombs

Definitions

  • the present invention relates to a device for triggering a command such as arming command on a mobile machine under given conditions, in particular speed.
  • Another means consists in using a pyrotechnic means but here again it is necessary to take into account the physical parameters in particular the speed and to place safeties auxiliaries.
  • the object of the present invention is to propose a mechanical device for triggering a command on a vehicle flying at a determined minimum speed, characterized in that it comprises a housing linked to the body of the vehicle, the removable cover of which is provided with a blocking means is ejected under the effect of an elastic means, a parachute connected to a coiled halyard and held by bumps to break, a return means linked to the command, a fuse-type connection between this parachute and this means of reference.
  • This cover is further characterized in that the cover is held in place by three pins through which pass pins, erasable by a rotary lever, this lever being subjected to the action of a pyrotechnic means.
  • the return means consists of pulleys pivoting about their axis by a mounting with ball bearings, a slide with stop.
  • FIG. 1 we see the following device 1 the invention comprising a chassis 2.
  • This chassis consists of two parts: a box 3 fixed to the body of the machine to be controlled (not shown) fixed at 4 and 5 by screwing, - a cover 6 comprising three pins 7 and 8 secured to the upper part of this cover. These pins have a lower bore in the lower end part such as 9 and 10.
  • pins 11 and 12 are respectively introduced, the ends 13 of which are mounted on an axis 14.
  • This axis is carried by the end of a lever 15 itself pivoting on an axis 16, the other end 17 of this lever being connected to a control device, for example pyrotechnic (not shown).
  • the pivoting is indicated by the arrow 18 and the position of the ends 13 is referenced at 130 and shown in broken lines.
  • the pin 12 of greater length is supported and guided by an intermediate support 19.
  • a return means 20 consisting of two pulleys 21, 22 mounted on axes with ball bearings 23, 24.
  • a halyard 25 is mounted on these two muffle pulleys, it connects the control pin 26 of the machine to be controlled to the end 27 of a slide 28. This has an oblong bore 29 sliding around a fixed pin 30.
  • a fuse link 31 is fixed on the one hand to the end 32 of the slide 28 and on the other hand to the lines of a parachute 33 placed in the folded position between the cover 6 and the frame 2, after this fuse link is passed through a pulley 34 secured to the housing 3.
  • Elastic means more particularly helical springs 35, 36 are threaded on the pins 7 and 8.
  • skirts 37, 38 made of flexible elastomer surround these springs.
  • the end of the cover 6 can take a particular shape at at least one of its ends 60 by which the cover is retained in its closed position by means of flaps or wings not shown connecting the cover 6 with the housing 3, so that the cover cannot be ejected without the flaps being opened, or the wings being deployed for example In this case, the flaps or the wings mechanically block the cover by simply pressing the end 60, and must be removed before the cover is ejected.
  • FIG. 3 we see the cover 6 ejected with the springs 35 and 36 relaxed and protected by the skirts.
  • the arrow 41 indicates the direction of ejection and the arrow 42 indicates the withdrawal of the parachute casing 43.
  • the halyard 70 is of sufficient length to allow deployment of the parachute and good wind resistance.
  • the ignited pyrotechnic device pivots the lever 15 about its axis 16 which leads to the withdrawal of the two pins 11 and 12.
  • the cover 6 is ejected under the effect of the three springs such as 35.36.
  • the tensile force is sufficient to remove the parachute casing 43, the parachute 33 can be deployed and the tensile force is a function of the speed of the machine so that when this speed is sufficient, the effort is sufficient to break one by one the bumps to be broken 71.
  • the halyard 70 is completely dislodged, it then causes the fuse link 31 who slides the slide 28 which in turn drives the halyard 25 which translates the control 26.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
EP88401669A 1987-07-09 1988-06-29 Steuerungsvorrichtung für die Scharfstellung einer Rakete oder ähnlichen beweglichen Gegenständen Withdrawn EP0302766A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8709769A FR2617994B1 (fr) 1987-07-09 1987-07-09 Dispositif de commande d'une fonction d'un engin mobile
FR8709769 1987-07-09

Publications (1)

Publication Number Publication Date
EP0302766A1 true EP0302766A1 (de) 1989-02-08

Family

ID=9353038

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88401669A Withdrawn EP0302766A1 (de) 1987-07-09 1988-06-29 Steuerungsvorrichtung für die Scharfstellung einer Rakete oder ähnlichen beweglichen Gegenständen

Country Status (2)

Country Link
EP (1) EP0302766A1 (de)
FR (1) FR2617994B1 (de)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1894954A (en) * 1932-04-15 1933-01-24 Lee P Johnson Aerial flare
US3749017A (en) * 1971-12-07 1973-07-31 Us Navy Parachute retarding tail assembly for bomb
US3817179A (en) * 1966-07-21 1974-06-18 Us Navy Parachute pack with release mechanism
FR2443663A1 (fr) * 1978-08-31 1980-07-04 Matra Perfectionnements aux bombes d'aviation et a leur dispositif d'activation

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1894954A (en) * 1932-04-15 1933-01-24 Lee P Johnson Aerial flare
US3817179A (en) * 1966-07-21 1974-06-18 Us Navy Parachute pack with release mechanism
US3749017A (en) * 1971-12-07 1973-07-31 Us Navy Parachute retarding tail assembly for bomb
FR2443663A1 (fr) * 1978-08-31 1980-07-04 Matra Perfectionnements aux bombes d'aviation et a leur dispositif d'activation

Also Published As

Publication number Publication date
FR2617994A1 (fr) 1989-01-13
FR2617994B1 (fr) 1991-02-15

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