EP0421873A1 - Vorrichtung zum Abbremsen von Bomben nach Abwurf aus einem Flugzeug - Google Patents

Vorrichtung zum Abbremsen von Bomben nach Abwurf aus einem Flugzeug Download PDF

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Publication number
EP0421873A1
EP0421873A1 EP90402733A EP90402733A EP0421873A1 EP 0421873 A1 EP0421873 A1 EP 0421873A1 EP 90402733 A EP90402733 A EP 90402733A EP 90402733 A EP90402733 A EP 90402733A EP 0421873 A1 EP0421873 A1 EP 0421873A1
Authority
EP
European Patent Office
Prior art keywords
bomb
propellant
cap
cover
jet
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.)
Granted
Application number
EP90402733A
Other languages
English (en)
French (fr)
Other versions
EP0421873B1 (de
Inventor
Michel Mulleman
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to AT90402733T priority Critical patent/ATE89073T1/de
Publication of EP0421873A1 publication Critical patent/EP0421873A1/de
Application granted granted Critical
Publication of EP0421873B1 publication Critical patent/EP0421873B1/de
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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • 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

Definitions

  • the invention relates to the dropping of bombs or other munitions from an aircraft and, more particularly, the control of the trajectory of the bombs after they have been dropped.
  • braking ensures the bomb better stability of its trajectory and, by increasing its angle of impact with respect to the ground, eliminates the risks of ricochet and gives it increased efficiency.
  • the object of the present invention is to remedy the drawbacks presented by known devices for braking bombs dropped from an aircraft and to this end it provides a device which, while being very simple, reliably ensures braking. effective of the bomb as soon as it is dropped.
  • the braking of the dropped bomb is ensured by a propellant associated with the bomb and whose gas jet is oriented towards the front of the latter to ensure a back-propelling effect.
  • the orientation of the jet of the propellant towards the front can, for example, be obtained by a system comprising pipes connected to the output of the propellant and wrapped in a cap supporting hatches which are deployable, under the action of the jet, between a retracted position corresponding to the state of rest of the propellant device and a forward inclined position orienting in this direction the jet leaving said pipes.
  • the orientation of the jet of the propellant can also be obtained by means of pipes, wrapped in a cap, which are connected to the output of the propellant and open in the extension of the bomb stabilization fins.
  • the front part of these fins is then closed by a material degradable under the effect of heat (eutectic alloy, synthetic resin) so that, when the propellant is at rest, the fins retain their aerodynamic profile and that, during the ignition of the propellant, the material is destroyed by allowing the evacuation of gases towards the front of the bomb.
  • the cap which envelops the device ensuring the forward orientation of the jet of the propellant can be automatically ejected, when the bomb has reached a predetermined position, thus causing the propulsion of the bomb in the terminal phase of its trajectory to communicate. to it an additional energy improving its effectiveness on impact against hardened objectives.
  • FIG. 1 there is shown in 1 the body of a bomb carrying at its rear part stabilizing fins 2.
  • the body 1 is equipped at its rear end of a propulsion system 3, the dimensional characteristics of which are adapted to those of the bomb.
  • a jet manifold 5 which has several pipes 6 and which is enveloped by a cap 7 conforming to the external profile of the bomb 1.
  • the cap 7 is held in position by means cables 8 which run inside the stabilization fins 2.
  • an equipment compartment 9 in which is housed a pyrotechnic device 10 connected to the cables 8 and cooperating with a device 11 measuring the speed of the bomb and selectively controlling the actuation of the pyrotechnic device 10 to ensure the cutting of the cables 8 and therefore the ejection of the cap 7.
  • the hatch 13 On the cover 7 are articulated, around axes 12, hatches 13 designed to take a retracted position before the ignition of the propulsion device 3 and to come to deploy forward under the effect of the pressure exerted by the jet leaving the pipe 6 with which the hatch 13 is associated.
  • the hatch 13 is articulated at its lower part, by an axis 14, to a moving part 15 of substantially triangular shape and comprises, also at its lower part, an axis 16 designed to cooperate with a extension 17 of the upper part of the part 15 so that the rise of the hatch 13 leads to that of the part 15.
  • the part 15 At its lower part the part 15 also has an extension 18 intended, at the end of the opening pivoting of the hatch 13, coming into abutment against a fixed part 19 to limit the pivoting of the hatch 13.
  • the pyrotechnic device After a predetermined period of time, corresponding to a drop in the speed of the bomb measured by the device 11, the pyrotechnic device is automatically controlled to ensure the cutting of the cables 8 and therefore the ejection of the cap 6 and the hatches 13 carried by it. Bomb 1 is thus propelled in the final part of its trajectory, which makes it possible to increase its impact effectiveness against hardened targets.
  • FIG. 4 to 6 there is shown a second embodiment of the device according to the invention.
  • a propellant device 23 comprising a nozzle 24 in the extension of which is disposed the jet manifold 25 with several pipes 26.
  • the manifold 25 is enveloped by the cap 27 which follows the external profile of the bomb 21 and which is held in position by the cables 28 traveling inside the fins 22 for stabilizing the bomb 21.
  • the pyrotechnic device connected to the cables 28 and housed inside the box with equipment 29, and at 31 the device measuring the speed of the bomb 21.
  • each pipe 26 forms a bend to be oriented towards the front of the bomb, and cooperates with the rear end of a fin 22 which serves as a final conduit.
  • the front part 32 of each fin 22 is closed by a thermally degradable material so that these fins maintain their aerodynamic profile during the ballistic phase of the trajectory, then that this material is then destroyed during the firing of the propellant device 23 thus allowing the evacuation of gases towards the front of the bomb and therefore the desired effect of back-propelling braking.
  • the measuring device 31 and the pyrotechnic device 30 control the cutting of the cables 28, and therefore the ejection of the cap 27 and of the conduits 26 which it maintains, so that the bomb is propelled during the final part of its trajectory.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid Mechanics (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Regulating Braking Force (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
  • Braking Systems And Boosters (AREA)
  • Braking Arrangements (AREA)
  • Valves And Accessory Devices For Braking Systems (AREA)
  • Jet Pumps And Other Pumps (AREA)
EP90402733A 1989-10-04 1990-10-03 Vorrichtung zum Abbremsen von Bomben nach Abwurf aus einem Flugzeug Expired - Lifetime EP0421873B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT90402733T ATE89073T1 (de) 1989-10-04 1990-10-03 Vorrichtung zum abbremsen von bomben nach abwurf aus einem flugzeug.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8912954A FR2652641B1 (fr) 1989-10-04 1989-10-04 Dispositif pour le freinage d'une bombe apres son largage d'un aeronef.
FR8912954 1989-10-04

Publications (2)

Publication Number Publication Date
EP0421873A1 true EP0421873A1 (de) 1991-04-10
EP0421873B1 EP0421873B1 (de) 1993-05-05

Family

ID=9386071

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90402733A Expired - Lifetime EP0421873B1 (de) 1989-10-04 1990-10-03 Vorrichtung zum Abbremsen von Bomben nach Abwurf aus einem Flugzeug

Country Status (5)

Country Link
EP (1) EP0421873B1 (de)
AT (1) ATE89073T1 (de)
DE (1) DE69001532T2 (de)
ES (1) ES2041516T3 (de)
FR (1) FR2652641B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2702556A1 (fr) * 1993-03-08 1994-09-16 Giat Ind Sa Tête militaire incendiaire.
CN111023916A (zh) * 2019-12-31 2020-04-17 蓝箭航天空间科技股份有限公司 一种箭体连接器捕获装置

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2539643A (en) * 1946-05-08 1951-01-30 William R Smythe Apparatus for decelerating torpedoes
US2637164A (en) * 1945-03-22 1953-05-05 Power Jets Res & Dev Ltd Jet spoiling means for aircraft gas turbines
US3058304A (en) * 1959-03-02 1962-10-16 Thompson Ramo Wooldridge Inc Steering control for rocket
DE2803036A1 (de) * 1978-01-25 1979-07-26 Messerschmitt Boelkow Blohm Gelenkte bombe fuer den tiefflugeinsatz

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3177655A (en) * 1961-01-24 1965-04-13 Thiokol Chemical Corp Rocket motor thrust termination and reversal device

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2637164A (en) * 1945-03-22 1953-05-05 Power Jets Res & Dev Ltd Jet spoiling means for aircraft gas turbines
US2539643A (en) * 1946-05-08 1951-01-30 William R Smythe Apparatus for decelerating torpedoes
US3058304A (en) * 1959-03-02 1962-10-16 Thompson Ramo Wooldridge Inc Steering control for rocket
DE2803036A1 (de) * 1978-01-25 1979-07-26 Messerschmitt Boelkow Blohm Gelenkte bombe fuer den tiefflugeinsatz

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2702556A1 (fr) * 1993-03-08 1994-09-16 Giat Ind Sa Tête militaire incendiaire.
CN111023916A (zh) * 2019-12-31 2020-04-17 蓝箭航天空间科技股份有限公司 一种箭体连接器捕获装置

Also Published As

Publication number Publication date
ATE89073T1 (de) 1993-05-15
FR2652641B1 (fr) 1994-04-29
EP0421873B1 (de) 1993-05-05
DE69001532D1 (de) 1993-06-09
FR2652641A1 (fr) 1991-04-05
ES2041516T3 (es) 1993-11-16
DE69001532T2 (de) 1993-12-02

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