EP1947415B1 - Dispositif pour le déploiement d'une surface portante - Google Patents

Dispositif pour le déploiement d'une surface portante Download PDF

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Publication number
EP1947415B1
EP1947415B1 EP08000525A EP08000525A EP1947415B1 EP 1947415 B1 EP1947415 B1 EP 1947415B1 EP 08000525 A EP08000525 A EP 08000525A EP 08000525 A EP08000525 A EP 08000525A EP 1947415 B1 EP1947415 B1 EP 1947415B1
Authority
EP
European Patent Office
Prior art keywords
wing
folding
longitudinal axis
base body
support surface
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.)
Not-in-force
Application number
EP08000525A
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German (de)
English (en)
Other versions
EP1947415A1 (fr
Inventor
Michael Feuerstein
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.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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 Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP1947415A1 publication Critical patent/EP1947415A1/fr
Application granted granted Critical
Publication of EP1947415B1 publication Critical patent/EP1947415B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • the invention relates to a device for wing deployment and a folding wing with such a device, in particular for a missile.
  • a missile such as a guided missile for use in a defense system, typically has wings or stabilizing surfaces projecting from its longitudinal body which provide the aerodynamic characteristics required for the flight phase. Such supporting or stabilizing surfaces are more hindering for the storage, for the transport or for the launch of such a missile. For this reason, folding wings are used, which are folded in the ground state of the missile and are deployed only in the flight phase.
  • Such a folding wing usually comprises a pivotable wing and is provided with a device which triggers the unfolding or deployment of the wing at the beginning of the flight phase.
  • a folding wing with such a device for airfoil deployment is subject to boundary conditions in terms of size and mass, since the folding wing in the folded state may increase the predetermined outer contour of the missile at most only insignificantly. Also, the wing of the missile may not increase the mass of the missile to an extent detrimental to the flight phase or range.
  • Such a device for wing deployment is from the document EP 06 902 84 B1 known.
  • a device for wing deployment for a folding wing of a guided missile wherein the wing belonging to the wing is stored in a longitudinally applied to the missile wing pocket.
  • the wing is swung out by using mechanical and / or pyrotechnic aids.
  • a first object of the invention is to provide a device by which the deployment process of a folding wing under the restriction of the low integration volume is effected as reliably as possible, if possible to effect without affecting the flow behavior after the deployment process.
  • Another object of the invention is to provide a folding wing, which shows the most reliable deployment during the flight phase and requires the lowest possible integration volume.
  • a third object of the invention comprises the representation of a missile which has the aerodynamic properties required under conditions of use.
  • the first object is achieved according to the invention by providing a device for aerofoil deployment, in particular for a missile, with a base body extending along a longitudinal axis, with a fastening means, with a number of movable flaps and with a number of lateral recesses, wherein the fastening means for Positioning of the base body is formed on a front end side of a support surface, wherein the or each movable flap for influencing the flow resistance of the support surface or the control surface is formed, and the or each lateral recess for self-releasable attachment of the body to the support surface or the control surface set in an end position is.
  • the invention is based in a first step on the idea of using flaps on the wings, which increase the flow resistance of the wing and thereby effectively support their unfolding up to the final position. This causes a reliable unfolding.
  • the invention recognizes that the enlargement of the flow resistance, which is advantageous in itself for the unfolding process, is disadvantageous for the aerodynamic properties of the flying object.
  • the flight behavior of the missile is significantly affected. The missile slows down, slows down, and reduces range, or increases fuel requirements to compensate for reduced range and speed.
  • the invention is based on the idea of triggering a self-solution of the attachment of the device to the support surface when the end position is reached.
  • An increase in the flow resistance is thus selectively and effectively used only for the deployment process.
  • the wing performance parameters are determined by the device, i. in particular, no longer adversely affected by the valves arranged thereon, since it is then no longer present.
  • the use of pyrotechnic elements is unnecessary.
  • the detached from the wing when reaching the intended end position device is lifted by their increased flow resistance of the wing in a controlled manner and moves away in the desired manner from the missile. A collision with the missile is not to be feared.
  • the device for airfoil unfolding is advantageously characterized in that the fastening means comprises a longitudinal recess, which has a corresponding to the front end of the support surface negative mold. With such a longitudinal recess, the base body can fit accurately on the front end side of the support surface.
  • the base body advantageously on one end side on a Entrastungssch, in particular a bevel, which / s gives the base body a pulse along its longitudinal axis, in particular in the direction of the opposite end side of the body.
  • This stop is in particular to be coupled with the achievement of the predetermined end position. If the support surface is unfolded during the unfolding process up to the end position, the unlocking means runs against the stop when the end position is reached, whereby the unlocking means is released. If the unlocking by a pulse along the longitudinal direction, the device for wing deployment is moved away from the missile. The triggering by a longitudinal movement of the body is additionally supported by the inertia of the body.
  • the unlocking means is effected in that the or each lateral recess is designed such that a displacement of the device from a predetermined end position along the longitudinal axis, a solution of the attachment is triggered.
  • the or each recess is hook-shaped, so that the device can be fixed in particular in the end position with locking bolts.
  • the locking bolts are suitably assigned to the wing.
  • the hook shape of the or each recess allows a longitudinal displacement of the base body such that in a holding position of the base body is fixed to the support surface and in a relation to the holding position by a minimum length in the longitudinal shifted position, the fixation is achieved.
  • a plurality of recesses are provided which have a different length and shape depending on the position with respect to the longitudinal axis. For example, can be achieved with two lateral recesses of different lengths, which are positioned spaced apart along the longitudinal axis, that the detachment of the support surface from the side recesses takes place at different times, so that the main body at the moment of detachment from the wing to this a certain Angle forms.
  • pairs movable flaps along the longitudinal axis are arranged opposite one another. If the device is mounted on a support surface, these movable flaps serve to symmetrically increase the flow resistance of the support surface on both sides of the surface. By deliberately increasing the flow resistance of the wing, the wing is unfolded reliably in the unfolding process.
  • the flaps are provided with a spring mechanism, which is set up at a release for setting up the flaps. Since the flaps are placed by their flow resistance, a relatively simple spring mechanism, for example, using a mechanical compression or tension spring, to complete setting up the flaps to increase sufficient the flow resistance and thus to achieve the deployment of the folding wing or the wing.
  • the choice of a suitable material is advantageous, which has the properties required for use, but which is still inexpensive to produce. Above all, plastics are suitable for this purpose.
  • a folding wing is specified, in particular for a missile, with a support surface, with a pivot mechanism for extending the wing to an end position, with a wing pocket for longitudinal recording of the wing in a retracted state, and with a arranged at the front end of the wing device for wing deployment of the aforementioned type.
  • such a folding wing is designed such that the support surface is not completely enclosed by the pocket in the retracted state and the device for aerofoil deployment is applied to the projecting from the pocket front end.
  • a number of locking bolts are preferably arranged for fixing the device to the support surface.
  • Each of these locking bolts engages in the respective corresponding lateral recess of the device for aerodynamic development positively or positively.
  • the or each locking bolt may be resiliently mounted. In this way, and furthermore advantageously, constraints can be imposed by the interaction of the or each locking bolt with the or each corresponding lateral recess of the device, so that the movement of the device during the detachment process is guided in a desired manner. In an application during the detachment process, for example, the device rather dissolves from those locking bolts which are closer to the pivot point of the support surface than from further spaced locking bolts.
  • the device rotates during the detachment process to the more distant locking bolt before it dissolves completely.
  • This process is supported by flaps which increase the flow resistance.
  • a partial rotation of the body are coupled with its translational detachment movement so that the main body includes in the separation of the support surface with this a certain angle.
  • a controlled release which is achieved by specifying the coupling of the degrees of freedom of the detachment movement, is advantageous to prevent irregular movements of the body during the detachment and thus a possible collision with the flying object.
  • the flap relate to its interaction and arrangement to the or each movable flap of the device for wing deployment.
  • a flap engages in the retracted state of the support surface in the wing pocket and is held there in particular under bias, so that the flap is retracted itself.
  • the flap In the erected state, the flap lies substantially in the plane of the longitudinal axis of the device and is perpendicular to the support surface.
  • the folding wing advantageously has a suitable release mechanism by which the support surface is quickly moved out of the wing pocket so far that the or each movable flap is no longer in interaction with the wing pocket and is no longer biased by the latter.
  • a triggering mechanism can be realized via an actuator or a spring mechanism. In particular, this does not have to be designed to open the wing up to the end position and can therefore be designed to save space and integrated in the area of the wing pocket.
  • the folding wing is advantageously equipped with a sensor-actuator system which triggers a release pulse in the extended state of the support surface in the region of the end position, which is transmitted to the base body of the device for airfoil unfolding.
  • a sensor-actuator system can act in addition.
  • the device is released from its anchorage in addition to the inertia of the body.
  • the third object of the invention is achieved by a missile which is equipped with a number of folding wings of the type described above.
  • a device for wing deployment and a folding wing of the type described above are in principle also suitable for use on underwater projectiles or diving vehicles, the concrete shape of the device and acting as a rudder flap are to be adapted to the specific hydrodynamic requirements.
  • Fig. 1 shows a device V for wing deployment with a base body 1 and with movable flaps 2, which is applied to a pivotable support surface 3 of a folding wing 4.
  • the folding wing 4 comprises in addition to the pivotable support surface 3, a wing pocket 5, which includes the pivotable support surface 3 in the folded state shown here.
  • the region of the end face 6, on which the device 1 rests projects out of the wing pocket 5 and the movable flaps 2 of the device engage in the wing pocket 5 at the end.
  • the movable flaps 2 are provided with a spring mechanism for unfolding so as to be biased by the wing pocket 5 in the illustration shown.
  • the folding wing 4 comprises a fastening strip 7, on which the folding wing 4 is mounted on the missile. The folding wing 4 is thus mounted longitudinally on a missile, not shown, so that the folding wing 4 unfolds with respect to the missile in the radial direction to the outside.
  • Fig. 2 is the folding wing 4 with the device V to Fig. 1 shown with initial swung-out wing 3 in a side view.
  • the support surface 3 during the flight phase of the in Fig. 1 shown folded state blown out.
  • the leverage of the spring mechanism is not sufficient to swing out the wing 3 completely.
  • the illustration shows the flaps 2 at the moment of unfolding, with the wing just enclose an angle of about 45 °.
  • Fig. 3 shows the folding wing 4 with the device V for wing deployment after Fig. 1 with swung-out wing 3 just before reaching the End position in perspective view according to Fig. 1 , Visible are the unfolded hinged flaps 2 on both sides of the support surface 3, which is almost perpendicular to the wing pocket 5.
  • the longitudinal direction 10 of the wing pocket 5 corresponds to the inflow direction of the wing 3, so that the movable flaps 2 generate a maximum flow resistance in the unfolded state.
  • the support surface 3 from the in Fig. 2 illustrated pivot state erected to the state shown here. It can be seen that such a flow resistance after the opening process affects the flight behavior of the missile.
  • Fig. 4 now adjusts the folding wing 4 with the device V.
  • Fig. 1 in the too Fig. 3 identical configuration in side view. More details are Fig. 2 removable.
  • the lower end side 1A of the base body 1 of the device V runs against a stop 11.
  • a beveled ramp surface at the lower end of the base body 1 of the device V this is a pulse along the direction 12, ie in the longitudinal direction of the basic body 1, which is reinforced by the inertia of the device V even more.
  • Fig. 5 adjusts the folding wing with initial detaching device Fig. 1 with fully swung-out wing in the final position in lateral view. Further details of the presentation are Fig. 4 such as Fig. 2 removable. The situation presented here follows directly on in Fig. 4 illustrated situation. As a result of the pulse triggered toward the stop, the device V on the lower lateral recesses 8A is disengaged from the corresponding lower locking pins 9A, which are arranged on both surface sides of the support surface 3.
  • the base body 1 By notching the recesses 8B from the locking pin 9B, the base body 1 is rotated further, thereby rotating on the upper recesses 8C about the upper, spring-mounted locking pin 9C. After a predetermined angle of rotation, which is determined by the shape of the recesses 8C, the device V latches off the support surface 3 completely and is carried away by the flow. Due to the detachment, in which the longitudinal axis of the main body 1 forms a certain angle with the longitudinal axis of the supporting surface 3, a collision of the device V with the flying object on which the folding wing 4 is mounted is avoided after detachment.
  • Fig. 7 is the folding wing 4 with the device for Tragentertfaltung after Fig. 1 after triggering the detachment pulse with detailed representations of the detachment process shown.
  • the overall presentation corresponds to the situation directly related to the in Fig. 4 The situation shown follows, in the moment in which the release pulse was triggered.
  • the wing 3 is already in its final position.
  • the partial figures A and B show details of the recesses 8A and 8B, 8C, respectively, with the corresponding locking bolts 9A, 9B, 9C.
  • a chamfer 13 is visible on the lower end side 1A of the base body 1 of the device V as the unlocking means, which deflects the impact impulse of the base body 1 against the stop 11 into a detachment pulse along the longitudinal direction of the base body.
  • the end side of the recess 8A is already shifted relative to the corresponding locking pin 9A.
  • the corresponding displacement of the recess 8B is visible relative to the locking bolt 9B.
  • the base body 1 is further connected via the locking bolt 9C with the support surface 3.
  • Fig. 8 is the folding wing 4 with initially peeling device after Fig. 5 shown with detailed representations of the detachment process.
  • the overall presentation corresponds to the situation in Fig. 5 ,
  • the subfigures Detail C and Detail D show the same details of the subfigures Detail A and Detail B Fig. 7 but at the time of the in Fig. 5 equivalent.
  • the unlatching movement of the locking bolt 9B begins from the recess 8B, visible in partial detail D.
  • the device V rotates by the lever effect of the flow resistance on the erected movable flaps 2 on the recess 8C to the locking pin 9C.
  • the main body 1 of the device V detaches from the support surface 3.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Toys (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Transmission Devices (AREA)
  • Refuge Islands, Traffic Blockers, Or Guard Fence (AREA)

Claims (20)

  1. Dispositif (V) pour le déploiement d'une surface portante, notamment pour un missile, comprenant un corps de base (1) s'étendant le long de l'axe longitudinal du dispositif, un moyen de fixation, une pluralité de volets mobiles (2) et une pluralité d'évidements latéraux (8), le moyen de fixation étant réalisé pour placer le corps de base (1) sur un côté d'extrémité frontale (6) d'une surface portante (3), le ou chaque volet mobile (2) étant réalisé pour influencer la résistance d'écoulement de la surface portante (3), et le ou chaque évidement latéral (8) étant prévu pour fixer de manière détachable automatiquement le corps de base (1) sur la surface portante (3) dans une position de fin de course.
  2. Dispositif (V) selon la revendication 1,
    dans lequel le moyen de fixation comprend un évidement longitudinal, qui présente une forme négative correspondant au côté d'extrémité frontale (6) de la surface portante (3).
  3. Dispositif (V) selon la revendication 1 ou 2,
    dans lequel le corps de base (1) présente au niveau d'un côté d'extrémité (1A) un moyen de désencliquetage qui confère au corps de base (1) lors de la venue en butée, une impulsion (12) le long de l'axe longitudinal du dispositif.
  4. Dispositif (V) selon la revendication 3, dans lequel le ou chaque évidement latéral (8) est réalisé de telle sorte que dans le cas d'un déplacement du dispositif (V) dans la position de fin de course le long de l'axe longitudinal, un desserrage de la fixation ait lieu.
  5. Dispositif (V) selon la revendication 4,
    dans lequel le ou chaque évidement (8) est réalisé en forme de crochet de sorte que le dispositif puisse notamment être fixé avec des boulons de verrouillage (9) dans la position de fin de course.
  6. Dispositif (V) selon la revendication 4 ou 5, dans lequel plusieurs évidements sont disposés le long de l'axe longitudinal du dispositif, dont la forme, notamment pour influencer l'opération de détachement, est à chaque fois différente en fonction de la position le long de l'axe longitudinal.
  7. Dispositif (V) selon l'une quelconque des revendications 1 à 6,
    dans lequel des volets (2) à chaque fois opposés par paires, sont disposés le long de l'axe longitudinal.
  8. Dispositif (V) selon l'une quelconque des revendications 1 à 7,
    dans lequel les volets (2) sont pourvus d'un mécanisme à ressort qui est prévu pour le montage des volets (2) dans le cas d'un déclenchement.
  9. Dispositif (V) selon l'une quelconque des revendications 1 à 8,
    qui est fabriqué en plastique.
  10. Empennage repliable (4), notamment pour un missile, comprenant une surface portante (3), avec un mécanisme de pivotement pour le déploiement de la surface portante (3) jusque dans une position de fin de course, un compartiment (5) de surface portante pour recevoir du côté longitudinal la surface portante (3) dans un état replié et un dispositif (V) disposé sur le côté d'extrémité frontale (6) de la surface portante (3) pour le déploiement de la surface portante selon l'une quelconque des revendications précédentes.
  11. Empennage repliable (4) selon la revendication 10, dans lequel la surface portante (3), dans l'état replié, fait saillie au moins avec le côté d'extrémité frontale (6) hors du compartiment (5) de surface portante et le dispositif (V) pour le déploiement de la surface portante est appliqué sur le côté d'extrémité frontale saillant (6).
  12. Empennage repliable (4) selon la revendication 11, dans lequel le dispositif (V) pour le déploiement de la surface portante est fixé à l'aide d'un certain nombre de boulons de verrouillage (9), et le ou chaque boulon de verrouillage (9) vient en prise par engagement par force ou par correspondance géométrique dans le ou chaque évidement (8) latéral correspondant du dispositif (V).
  13. Empennage repliable (4) selon la revendication 12, dans lequel le ou chaque boulon de verrouillage (9) est monté à ressort.
  14. Empennage repliable (4) selon la revendication 12 ou 13, dans lequel le ou chaque boulon de verrouillage (9) avec le ou chaque évidement latéral correspondant (8) du dispositif (V) est réalisé pour créer un guidage forcé au moins partiel du dispositif (V) dans le cas d'une opération de détachement.
  15. Empennage repliable (4) selon l'une quelconque des revendications 11 à 14,
    dans lequel le ou chaque volet (2) du dispositif (V), dans l'état replié de la surface portante (3), vient en prise du côté de l'extrémité dans le compartiment (5) de surface portante, en particulier y est fixé avec précontrainte.
  16. Empennage repliable (4) selon la revendication 15, dans lequel le ou chaque volet mobile (2) du dispositif, dans l'état monté, est disposé essentiellement dans le plan de l'axe longitudinal du dispositif (V) et perpendiculairement à la surface portante (3).
  17. Empennage repliable (4) selon la revendication 15 ou 16,
    dans lequel un mécanisme d'actionnement ou de ressort pour déployer par pivotement la surface portante (3) hors de l'état replié est prévu de telle sorte qu'après l'activation du mécanisme, aucun volet (2) ne soit plus en interaction avec le compartiment (5) de surface portante.
  18. Empennage repliable (4) selon l'une quelconque des revendications 10 à 17, dans lequel, dans l'état déployé de la surface portante (3), dans la région de la position de fin de course, une impulsion de détachement (12) est déclenchée par le biais d'un système de capteurs et d'actionneurs, laquelle est transmise au corps de base (1) du dispositif.
  19. Empennage repliable (4) selon l'une quelconque des revendications 10 à 18,
    dans lequel, dans l'état déployé de la surface portante (3), son axe longitudinal est essentiellement perpendiculaire à l'axe longitudinal du compartiment (5) de surface portante.
  20. Objet volant, notamment un missile dirigeable, comprenant une pluralité d'empennages repliables (4) selon l'une quelconque des revendications 10 à 19.
EP08000525A 2007-01-19 2008-01-12 Dispositif pour le déploiement d'une surface portante Not-in-force EP1947415B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007002948A DE102007002948B4 (de) 2007-01-19 2007-01-19 Vorrichtung zur Tragflächenentfaltung

Publications (2)

Publication Number Publication Date
EP1947415A1 EP1947415A1 (fr) 2008-07-23
EP1947415B1 true EP1947415B1 (fr) 2010-06-23

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08000525A Not-in-force EP1947415B1 (fr) 2007-01-19 2008-01-12 Dispositif pour le déploiement d'une surface portante

Country Status (5)

Country Link
US (1) US7919740B2 (fr)
EP (1) EP1947415B1 (fr)
AT (1) ATE472086T1 (fr)
DE (1) DE102007002948B4 (fr)
ES (1) ES2346484T3 (fr)

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DE102017113058A1 (de) 2017-06-14 2018-12-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät und Wiedereintritts-Fluggerät

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CN109631684A (zh) * 2018-11-28 2019-04-16 成都云鼎智控科技有限公司 一种单轴式机翼机构以及具备该机翼机构的发射体
CN109625243B (zh) * 2018-12-24 2021-08-17 湖南云箭集团有限公司 一种折叠翼面展开气动辅助驱动装置
CN111994266B (zh) * 2020-09-02 2023-05-30 广西大学 折叠翼扑翼机
US11592272B2 (en) * 2021-01-26 2023-02-28 Raytheon Company Aero-assisted missile fin or wing deployment system

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Publication number Priority date Publication date Assignee Title
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DE102017113058B4 (de) 2017-06-14 2023-04-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät

Also Published As

Publication number Publication date
DE102007002948A1 (de) 2008-07-31
ES2346484T3 (es) 2010-10-15
US7919740B2 (en) 2011-04-05
ATE472086T1 (de) 2010-07-15
DE102007002948B4 (de) 2009-04-02
US20090008496A1 (en) 2009-01-08
EP1947415A1 (fr) 2008-07-23

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