EP0319379B1 - Abwurfkörper mit aerodynamischen Bremsmitteln - Google Patents

Abwurfkörper mit aerodynamischen Bremsmitteln Download PDF

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Publication number
EP0319379B1
EP0319379B1 EP88402964A EP88402964A EP0319379B1 EP 0319379 B1 EP0319379 B1 EP 0319379B1 EP 88402964 A EP88402964 A EP 88402964A EP 88402964 A EP88402964 A EP 88402964A EP 0319379 B1 EP0319379 B1 EP 0319379B1
Authority
EP
European Patent Office
Prior art keywords
arms
launchable
body according
ground
launchable body
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
EP88402964A
Other languages
English (en)
French (fr)
Other versions
EP0319379A1 (de
Inventor
Jacques Picot
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 Group SAS
Original Assignee
Airbus Group 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 Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0319379A1 publication Critical patent/EP0319379A1/de
Application granted granted Critical
Publication of EP0319379B1 publication Critical patent/EP0319379B1/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
    • F42B23/00—Land mines ; Land torpedoes
    • F42B23/24—Details

Definitions

  • the present invention relates to a releasable body provided with aerodynamic braking means.
  • the releasable body according to the invention may constitute in particular, although not exclusively, a "submunition” intended to carry a military load (mine, rocket, minimissile, etc.). Such a body could also be brought to play a role of "sentinel", and for that purpose include means of observation and surveillance of the site.
  • a first aerodynamic braking problem therefore arises in order to minimize the impact effect on contact with the ground.
  • Such aerodynamic braking is commonly obtained using a parachute, as for example in document US-A3 875 862.
  • This nevertheless has a number of drawbacks.
  • the canvas of the parachute covering, on the ground, said body can limit the effectiveness of the sensors for detecting a potential target, and even prevent the start of the blow in the case of a rocket for example, or blind the means site observation and surveillance.
  • the lines of the parachute can get caught in the moving parts of the body and block its operation.
  • the surface spread on the ground of the parachute is likely to reveal the presence of said body, even if the parachute is ejected on arrival on the ground or immediately before.
  • the release body comprises, according to the preamble of claim 1, deployable arms articulated at one end of said body and actuation means intended to pass said arms during the descent aerial of said body, from a folded position along said body to a deployed position substantially perpendicular to said body in order to slow the descent of the latter.
  • the present invention relates to a releasable body of this type overcoming the aforementioned drawbacks.
  • the releasable body of the aforementioned type is characterized in that it comprises first means for controlling said actuation means for controlling the retraction of said arms along said body when the latter has reached the ground after its aerial descent , said body then being in standby state having its longitudinal axis at least substantially parallel to the surface of the ground, and second means for controlling said actuation means for controlling the deployment of said arms to pass from standby state to an active state in which the arms support the body on the ground.
  • document DE-A-3 127 071 describes a device comprising control means for changing from the braking state to the active state.
  • the structure of this last device, with inflatable arms, implies that the only possible evolution of the body does not allow any "turning back".
  • said arms of the releasable body in accordance with the present invention extend over substantially the entire length of said body, thereby facilitating the straightening of the body on the ground in the active state.
  • the body comprises three arms arranged at 120 ° from one another.
  • a skin of flexible material is provided between each pair of adjacent arms.
  • Said skin plays the role of parachute during the aerial descent of the body and, moreover, in the waking state of the body on the ground (arms folded), said skin surrounding the body can serve as camouflage and protection against the weather, for this one.
  • said actuating means comprise a motor capable of to drive an endless screw meshing with a toothed wheel provided at the articulation end of each of said arms.
  • said actuating means comprise a motor capable of driving an endless screw cooperating with a nut on which is mounted the articulation end of each of said arms.
  • the second control means are adapted to control the retraction of said arms to pass from the active state to the standby state.
  • said first control means can comprise at least one sensor capable of detecting the contact of said body with the ground
  • said second control means can comprise at least one sensor capable of detecting the presence of 'a potential goal.
  • the body comprises at least one sensor for detecting the release thereof for controlling the deployment of the arms after release.
  • said body may include a projectile provided with a military charge and / or means of observation and surveillance of the site.
  • Figure 1 is a schematic view of the releasable body, comprising aerodynamic braking means, according to the invention.
  • FIGS. 2 to 7 schematically illustrate the different phases of implementation of the releasable body of FIG. 1.
  • Figure 8 is a front view of an exemplary embodiment of the releasable body according to the invention, in the active state on the ground.
  • Figure 9 is a side view of Figure 8.
  • Figure 10 is a front view of another embodiment of the releasable body according to the invention, in the active state on the ground.
  • Figure 11 is a side view of Figure 10.
  • Figures 12 and 13 illustrate different means of actuating the arms of the releasable body of the invention.
  • the body 1 of the invention intended to be released, for example from an aircraft, is housed, before release, in a container 2 open at one end, and comprises aerodynamic braking means .
  • the latter consist of deployable arms 3, articulated at 4 at one of the ends of the body 1.
  • the body 1 comprises actuating means 5, described in more detail below, intended in particular to pass the arms 3 , during the aerial descent of the body 1, from a folded position along the body (Figure 1) to a deployed position substantially perpendicular said body ( Figure 3) to slow the descent of the latter.
  • a release sensor 6 is provided, for example a finger, disposed radially with respect to the axis of ejection of the body, which can move when the body 1 is released from its container 2.
  • a skin 7 of flexible material, fixed to the free end of the arms 3, can be provided between each pair of adjacent arms, which skin acts as a parachute.
  • Another possibility consists in using the arms 3 as a rotary wing so as to brake the aerial descent of the body 1.
  • the arms 3 are then profiled so as to form, once deployed, the blades of a rotor whose rotation ensures the aerodynamic braking of the body.
  • the body 1 comprises first control means 8 of the actuation means 5 for controlling the retraction of the arms 3 along the body l when the latter has reached the ground S after its aerial descent (FIG. 4), the body 1 being in the standby state when the arms 3 are in the fully folded position (FIG. 5).
  • second control means 9 of the actuation means 5 are provided for controlling the deployment of the arms 3 (FIG. 6) to pass from the standby state to an active state in which the arms 3 support the body 1 on the ground S (figure 7).
  • the second control means 9 can be adapted to control the retraction of the arms 3 to go from the active state ( Figure 7) to the standby state ( Figure 5).
  • the arms 3 advantageously extend over substantially the entire length of the body 1. In the standby state, this allows the body 1 to be completely camouflaged using the skins 7. In addition, this guarantees the recovery of the body 1 to pass from the waking state to the active state.
  • control means can be carried out in a logic unit 12, which the first 8 and second 9 control means share.
  • FIGS 8 to 13 illustrate in more detail embodiments of the body 1 of the invention.
  • the body 1, in the active state can rest on the free ends of the arms 3, playing the role of a tripod, by raising the body l above the ground.
  • the arms could also be placed on the ground over their entire length.
  • the actuation means 5 can comprise a motor 13, for example an electric motor, capable of driving an endless screw 14 meshing with a toothed wheel 15 provided at the articulation end of each of the arms 3.
  • the actuating means 5 can comprise a motor (not shown) capable of driving a worm 16, cooperating with a nut 17 on which is mounted, at 18, the the articulation end of each of the arms 3, the displacement of the arms 3 being, moreover, obtained by means of a bar 19, passing through a lumen 20 provided at said end of the arm 3, integral with the body 1.
  • the bodies 1 of the exemplary embodiments shown in FIGS. 8, 9 and 10, 11 comprise at least one projectile provided with a military charge and / or observation means and site monitoring 21, mounted in an articulated manner on a part 22 in the shape of a stirrup and which can take at least two positions, namely parallel to the longitudinal axis XX ′ of the body 1 and perpendicular thereto.
  • a skin 7 acting as a parachute can be provided between each pair of adjacent arms 3 (FIGS. 10 and 11), or the arms 3 can be shaped into blades 23 (FIGS. 8 and 9) and play the role of rotary wing.
  • FIGS. 8 and 9 has been shown, by way of example, provided with actuation means 5 of FIG. 12, and the body of FIGS. 10 and 11 of those of FIG. 13.
  • the body of the invention immediately after the body of the invention has been dropped from an aircraft, or pulled from a container on the ground, its arms are deployed to ensure its aerodynamic braking, in one or the other of the two ways indicated above, then, once on the ground, the arms fold up along the body and, if necessary, the skin or canvas, playing the role of parachute, treated appropriately, can completely cover it by camouflaging it and protecting it from the weather.
  • the body is then in a waking state.
  • the indicated sensors for example vibrations caused by the arrival of a tank
  • the body goes into alert or active state in the following way: the arms extend until a position such that they serve as a tripod, and the body firing position and waits. If the detected tank reaches its range, the projectile is fired. If, on the other hand, the tank moves away or goes out of range, the arms fold up and the body returns to standby state.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Folding Of Thin Sheet-Like Materials, Special Discharging Devices, And Others (AREA)
  • Forklifts And Lifting Vehicles (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (12)

  1. Abwurfkörper (1) mit an einem seiner Enden angebrachten entfaltbaren, angelenkten Armen (3) und Betätigungsmitteln (5), welche die genannten Arme (3) während des Falles des genannten Körpers durch die Luft aus einer längs des genannten Körpers eingefalteten Stellung in eine ausgefaltete, im wesentlichen zu dem genannten Körper senkrechte Stellung bringen, um den Fall des genannten Körpers zu bremsen,
    dadurch gekennzeichnet, daß er erste Mittel (8) zur Steuerung der genannten Betätigungsmittel (5), mit welchen das Wiederanlegen der genannten Arme (3) an den genannten Körper (1) gesteuert werden kann, wenn dieser nach seinem Fall durch die Luft den Boden erreicht hat, wonach der genannte Körper (1) in einem Bereitschaftszustand verbleibt, in welchem seine Längsachse zumindest im wesentlichen parallel zur Erdoberfläche ausgerichtet ist, und zweite Mittel (9) zur Steuerung der genannten Betätigungsmittel (5) umfaßt, mit denen das Ausfalten der genannten Arme (3) gesteuert werden kann, um aus dem Bereitschaftszustand in einen aktiven Zustand übergehen zu können, in welchem die Arme (3) den Körper (1) auf dem Boden tragen.
  2. Abwurfkörper gemäß Anspruch 1,
    dadurch gekennzeichnet, daß in eingefalteter Stellung die genannten Arme (3) im wesentlichen längs der gesamten Länge des genannten Körpers (1) anliegen.
  3. Abwurfkörper gemaß Anspruch 1 oder Anspruch 2,
    dadurch gekennzeichnet, daß er drei um 120° gegeneinander versetzte Arme (3) aufweist.
  4. Abwurfkörper gemäß einem der Ansprüche 1 bis 3,
    dadurch gekennzeichnet, daß zwischen je zwei benachbarten Armen (3) eine Haut (7) aus einem flexiblen Werkstoff vorgesehen ist.
  5. Abwurfkörper gemäß einem der Ansprüche 1 bis 4,
    dadurch gekennzeichnet, daß die genannten Betätigungsmittel (5) einen Motor (13) umfassen, welcher geeignet ist, eine Schnecke (14) anzutreiben, welche mit einem am Gelenkende jedes der genannten Arme (3) vorgesehenen Zahnrad (15) in Eingriff steht.
  6. Abwurfkörper gemaß einem der Ansprüche 1 bis 4,
    dadurch gekennzeichnet, daß die genannten Betätigungsmittel (5) einen Motor umfassen, welcher geeignet ist, eine Schnecke (16) anzutreiben, welche mit einer Mutter (17) zusammenwirkt, an welcher das Gelenkende jedes der genannten Arme (3) angebracht ist.
  7. Abwurfkörper gemäß einem der Ansprüche 1 bis 6,
    dadurch gekennzeichnet, daß die genannten zweiten Steuerungsmittel (9) geeignet sind, das Einfalten der genannten Arme (3) zu steuern, um vom aktiven Zustand in den Bereitschaftszustand überzugehen.
  8. Abwurfkörper gemäß einem der Ansprüche 1 bis 7,
    dadurch gekennzeichnet, daß die genannten ersten Steuerungsmittel (8) mindestens einen Sensor (10) umfassen, welcher geeignet ist, die Berührung des genannten Körpers (1) mit dem Erdboden festzustellen.
  9. Abwurfkörper gemäß einem der Ansprüche 1 bis 8,
    dadurch gekennzeichnet, daß die genannten zweiten Steuerungsmittel (9) mindestens einen Sensor (11) umfassen, welcher geeignet ist, die Anwesenheit eines möglichen Zieles festzustellen.
  10. Abwurfkörper gemaß einem der Ansprüche 1 bis 9,
    dadurch gekennzeichnet, daß er mindestens einen Sensor (6) umfaßt, welcher beim Abwurf des genannten Körpers (1) anspricht.
  11. Abwurfkörper gemäß einem der Ansprüche 1 bis 8,
    dadurch gekennzeichnet, daß er mindestens ein mit einer militärischen Ladung geladenes Geschoß (21) umfaßt.
  12. Abwurfkörper gemäß einem der Ansprüche 1 bis 11,
    dadurch gekennzeichnet, daß er Mittel (21) zur Beobachtung und Überwachung des Geländes umfaßt.
EP88402964A 1987-11-30 1988-11-24 Abwurfkörper mit aerodynamischen Bremsmitteln Expired - Lifetime EP0319379B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8716582 1987-11-30
FR8716582A FR2623773B1 (fr) 1987-11-30 1987-11-30 Corps largable muni de moyens de freinage aerodynamique

Publications (2)

Publication Number Publication Date
EP0319379A1 EP0319379A1 (de) 1989-06-07
EP0319379B1 true EP0319379B1 (de) 1992-09-09

Family

ID=9357307

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88402964A Expired - Lifetime EP0319379B1 (de) 1987-11-30 1988-11-24 Abwurfkörper mit aerodynamischen Bremsmitteln

Country Status (10)

Country Link
US (1) US4870904A (de)
EP (1) EP0319379B1 (de)
JP (1) JPH01167599A (de)
AU (1) AU609214B2 (de)
BR (1) BR8806389A (de)
CA (1) CA1314531C (de)
DE (1) DE3874494T2 (de)
ES (1) ES2035349T3 (de)
FR (1) FR2623773B1 (de)
IL (1) IL88423A (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2636419B1 (fr) * 1988-09-09 1993-10-01 Thomson Brandt Armements Projectile de neutralisation de zone, notamment d'aerodrome
DE4019148A1 (de) * 1990-06-15 1991-12-19 Dynamit Nobel Ag Flaechenverteidigungsmine mit vergroessertem wirkfeld
DE4023069A1 (de) * 1990-07-20 1992-01-23 Diehl Gmbh & Co Mine, insbes. panzerabwehrmine
DE4312286C2 (de) * 1993-04-15 2002-06-27 Dynamit Nobel Ag Militärische Waffe
GB2306147B (en) * 1995-10-13 1999-11-17 Marconi Gec Ltd Drag-producing aerodynamic device
EP2664945B1 (de) 2012-05-15 2015-07-08 The Boeing Company Unbeaufsichtigte Bodensensoren
US10676177B1 (en) * 2015-05-29 2020-06-09 Earthly Dynamics, LLC Robotic landing gear for rotorcraft

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1289702A (en) * 1917-02-06 1918-12-31 William Draper Dart.
US1626363A (en) * 1921-10-14 1927-04-26 Elmer A Sperry Gravity bomb
FR715385A (fr) * 1931-08-10 1931-12-02 Empennage repliable pour bombes d'aviation
US2044819A (en) * 1933-10-27 1936-06-23 James G Taylor Projectile
US3228634A (en) * 1963-07-18 1966-01-11 Chakoian George Air-drag apparatus for missiles
DE1800121C3 (de) * 1968-10-01 1981-06-11 Dynamit Nobel Ag, 5210 Troisdorf Vorrichtung zur definierten Positionierung von Abwurfkörpern, insbesondere Sprengladungen
US3948175A (en) * 1970-02-03 1976-04-06 Dynamit Nobel Aktiengesellschaft Warhead
BE795623A (fr) * 1972-02-18 1973-06-18 Dynamit Nobel Ag Mines a charge creuse pour usages multiples
US3978790A (en) * 1975-10-23 1976-09-07 The Boeing Company High altitude sonobuoy
US4492166A (en) * 1977-04-28 1985-01-08 Martin Marietta Corporation Submunition having terminal trajectory correction
DE3127071C2 (de) * 1981-07-09 1985-06-27 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Abwurfkörper
DE3322927A1 (de) * 1983-06-25 1985-01-03 Rheinmetall GmbH, 4000 Düsseldorf Von einem lastengeschoss oder flugkoerper abwerfbarer geschosskopf
DE3509282A1 (de) * 1985-03-15 1986-09-25 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Mine mit vertikaler oder horizontaler wirkrichtung

Also Published As

Publication number Publication date
BR8806389A (pt) 1989-08-22
AU609214B2 (en) 1991-04-26
DE3874494D1 (de) 1992-10-15
EP0319379A1 (de) 1989-06-07
FR2623773A1 (fr) 1989-06-02
US4870904A (en) 1989-10-03
DE3874494T2 (de) 1993-04-08
FR2623773B1 (fr) 1990-04-27
CA1314531C (fr) 1993-03-16
AU2566988A (en) 1989-06-08
JPH01167599A (ja) 1989-07-03
IL88423A (en) 1992-06-21
ES2035349T3 (es) 1993-04-16

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