EP0318359B1 - Vorrichtung zum Ausspreizen der Leitflügel eines Geschosses - Google Patents

Vorrichtung zum Ausspreizen der Leitflügel eines Geschosses Download PDF

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Publication number
EP0318359B1
EP0318359B1 EP88402880A EP88402880A EP0318359B1 EP 0318359 B1 EP0318359 B1 EP 0318359B1 EP 88402880 A EP88402880 A EP 88402880A EP 88402880 A EP88402880 A EP 88402880A EP 0318359 B1 EP0318359 B1 EP 0318359B1
Authority
EP
European Patent Office
Prior art keywords
fin
projectile
fact
deployment
mechanism according
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
EP88402880A
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English (en)
French (fr)
Other versions
EP0318359A1 (de
Inventor
André Blin
Alain Bonnet
Eric Crotet
Patrick Dauvergne
Bernard Masson
Evelyne Montet
Roger Crépin
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.)
Giat Industries SA
Original Assignee
Giat Industries SA
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 Giat Industries SA filed Critical Giat Industries SA
Publication of EP0318359A1 publication Critical patent/EP0318359A1/de
Application granted granted Critical
Publication of EP0318359B1 publication Critical patent/EP0318359B1/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
    • 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 is that of deployment devices for projectile fins, and more particularly for orientable fins, that is to say which can pivot in the deployed position under the action of a soup motor around a substantially perpendicular axis. to the axis of the projectile.
  • the deployable fins can only play a stabilizing role for a projectile animated by a slow or zero rotation movement, or also a guiding role, similar to that of the control surfaces for an airplane; in the latter case, they are controlled by a motor, itself controlled by an electronic assembly, they then make it possible to modify the trajectory of the projectile during its flight and therefore to correct possible aiming errors, or even to orient automatically, after detection of a target, the projectile towards it.
  • US-A-4,588,146 describes deployable fins for missile in a movement comprising a translation of the fins followed by two rotations.
  • the translation is carried out beforehand by an operator, which constitutes a risk of damage to the fins and consequently a malfunction of the assembly, causing destabilization of the missile.
  • the fins begin by presenting their largest surface facing the aerodynamic flow; the leading edge of the fins, the surface of which is smaller, being oriented in the direction of this flow only at the end of the deployment movement. It follows a braking of the projectile and a risk of destabilization all the more important as the asymmetries at the level of the movements of opening of the fins will be amplified by the importance of the forces which are exerted on them. The risk of destabilization will be even more critical in the case where the projectile is initially gyro-stabilized and where the deployment of the fins must allow it to adopt a regime stabilized by tailplane.
  • the invention applied to fins which have to provide a guiding function, also provides a means making it possible to completely control their opening movement as well as the instant of triggering of the latter, without however requiring an additional locking device.
  • the subject of the invention is a device for deploying a projectile fin between a carrying position, in which its plane is substantially parallel to the axis of the projectile, and a deployed position, the fin being made integral with the projectile by an articulation, device characterized in that the articulation is such that the deployment movement comprises at least two phases: a first in which the fin passes from the carrying position to a semi-deployed position, this passage being obtained by a rotation along a first axis which is perpendicular to the plane of the fin when the latter is in the position of takeout and a second in which the fin passes from the semi-deployed position to the deployed position, by a rotation along a second axis which is parallel to the plane of the fin.
  • the fin is moved by an actuator during all or part of the first phase of the deployment movement, and it is immobilized relative to the projectile by a locking means when it is in its carrying position.
  • the fin in the deployed position can pivot around the first axis under the action of a pilot motor, and this constitutes the actuator and / or the locking means .
  • the fin is secured to a support, itself immobilized relative to the inner ring of a bearing, the outer ring of this bearing being immobilized relative to the projectile, and on the other apart the motor is immobilized relative to the projectile and controls the rotation of the support by means of a coupling joint.
  • the fin may be moved by aerodynamic forces during the second phase of the deployment movement; in this case it may carry a pin, circulating during the first phase of the deployment movement in a circular groove immobilized relative to the projectile, the second phase intervening during the passage of the pin before a clearance of this groove.
  • the support will carry a lock immobilizing the fin relative to the latter in the deployed position.
  • a projectile 1 has at its rear part four fins 2, (shown schematically in the form of parallelepipeds to simplify the description), intended to provide both a stabilizing function and a guiding function; these fins are made integral with the projectile by joints 11, which will be described in detail below.
  • the projectile is fired by a weapon, not shown, and is gyro-stabilized during a first part of its trajectory, it therefore comprises known means and not shown here (such as a belt) such as to drive it in rotation during its journey to l inside the weapon.
  • This belt may be integral with the projectile itself or with a stationary cylindrical element relative to the projectile, and released on trajectory by pyrotechnic means (see for example patent W081 / 00908).
  • the fins 2 are shown in Figure 1 in the carrying position. They are immobilized relative to the projectile by a blocking means which will be described later.
  • the plane of the fin which is defined by an axis 8, materializing the main direction thereof, and an axis 7 orthogonal to the previous one, is substantially parallel to the axis 4 of the projectile.
  • This position is analogous to the carrying position described in patent US4664339.
  • the front end of each fin comes into a housing 3 in the body of the projectile 1.
  • Figure 2 shows the projectile with its fins without a semi-deployed position.
  • Figure 3 shows the projectile with the fins fully deployed.
  • the transition from the semi-deployed position to the deployed position (second phase of the deployment movement) is obtained by a rotation in the ⁇ direction, of each fin around a second axis 6, which is parallel to the plane of the 'fin.
  • the forces undergone by the fins are also reduced in substantially the same ratio, which makes it possible to reduce the mass of the fins in favor of the payload of the projectile, and to reduce shock and destabilizing asymmetries.
  • each fin being greater in direction 7 than in the direction normal to the plane of the fin (inertia ratio of the order of 60), the latter are less sensitive to the bending deformations induced by the aerodynamic forces.
  • This increase in the rigidity of the fins results in an increase in their natural vibration frequencies, which, in combination with the notable reduction in the forces to which they are subjected, makes it possible to guarantee a regular deployment movement of each fin, which reduces the risks destabilization of the projectile.
  • FIGS 4 and 5 show in detail the joint 11, the locking means and the actuator, which allow to obtain the two phases of the deployment movement described above, in this particular embodiment of the device according to invention.
  • Each fin 2 is made integral with a support 13 by means of a pivot 21 which materializes the second axis 6.
  • the mounting of the fin on the support is of the clevis-tenon type, the fin having one end constituting a clevis and the post being formed by the support 13. This type of arrangement made it possible to obtain better guidance of the fin during its deployment movement.
  • the fin is here shown in the carrying position with its plane parallel to the axis 4 of the projectile 1.
  • the support 13 is immobilized relative to the inner ring 16 of a bearing with two rows of angular contact balls.
  • the outer ring 15 of this bearing is immobilized by threading relative to a housing 12, itself secured to the projectile 1.
  • the bearing-bearing assembly thus constitutes the joint 11.
  • a motor 14, here an electric geared motor, is also immobilized relative to the box 12; in this particular embodiment, it is linked in translation to the housing by means of a shoulder of the latter and of the outer ring 15 of the bearing, and in rotation by pins not shown.
  • the motor 14 carries, on the upper part of its axis, a groove 20, and the support 13 a groove 19, these two grooves constitute, with an intermediate part 18, a seal of coupling, preferably a constant velocity joint, such as an Oldham joint here, which allows the motor 14 to drive the support 13, carrying the fin 2, in rotation around the first axis 5.
  • the coupling joint makes it possible to tolerate poor axial alignment when mounting the support and the motor, but it also makes it possible to isolate the latter from the vibrations which the fin could impart to it.
  • the bearing also makes it possible to isolate the engine from the aerodynamic forces which the fin will therefore transmit directly to the projectile 1, via the support and the bearing.
  • the fin carries a pin 22, one end of which is housed in a circular groove 24 carried by the housing. This circular groove ends with a clearance 27 (see FIG. 5), the usefulness of which will be specified below.
  • the support 13 also carries a lock 23, which is constituted by a finger 25, sliding against the action of a return spring, and which is intended to come into a housing 26 carried by the fin 2, this for the purpose to lock it in the deployed position at the end of the second phase of the deployment movement.
  • an encoder 17, of known type, and integral with the support 13, will make it possible to give an electronic control assembly, not shown, the information on the angular position of the fin 2 relative to the first axis 5.
  • the motor the main function of which is to guide the projectile by pivoting the deployed fin around the first axis 5
  • the actuator which causes the first phase of the deployment movement of the fin: its passage from the carrying position to the semi-deployed position.
  • the motor due to the irreversibility of the mechanical reducer which it comprises, also plays the role of means for blocking the fin in the carrying position.
  • the start of the opening is completely controlled and corresponds to the control of the motors; speeds and positions of the fins can be controlled by an electronic device, known per se, which will play individually on the control voltages of the different motors as a function of the information given by the encoders.
  • the control of the motors therefore makes it possible to accomplish the first phase of the deployment movement, which as has been seen previously will make it possible to obtain progressive braking of the rotation of the projectile; (but it is also possible to use other types of vanes of known type, such as those described in patent W081 / 00908, to cause braking in rotation, the deployment of the guide vanes then being controlled only when the speed of rotation has fallen below a certain value, of the order of 20 to 30 revolutions / second); when the fins are in the position of FIG. 2, the pin 22, which has circulated during the first phase of the deployment movement in the groove 24 and has thus maintained the fin in the plane defined by the axes 7 and 8, is then opposite the clearance 27.
  • the aerodynamic forces exerted on the fin are sufficient to rotate it around the second axis 6 and therefore to make it accomplish the second phase of the deployment movement, just until the locking of the fin; the engine then fulfilling its guiding role by pivoting the deployed fin around the first axis.
  • motors can be envisaged to fulfill both the function of actuator of the deployment movement of the fin, and the function of piloting the projectile; such as a pneumatic motor, powered by a gas reserve or else by a gas generator with pyrotechnic initiation.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Claims (10)

  1. Entfaltungsvorrichtung eines Flügels (2) eines Geschosses (1), zwischen einer Mitnahmestellung, in der seine Ebene ungefähr parallel zur Achse (4) des Geschosses verläuft, und einer entfalteten Stellung, wobei der Flügel mit dem Geschoß über ein Gelenk (11) ein einziges Teil bildet, dadurch gekennzeichnet, daß das Gelenk so geartet ist, daß die Entfaltungsbewegung zumindest zwei Phasen umfaßt:
    Eine erste Phase, in der der Flügel (2) von einer Mitnahmestellung in eine halb-entfaltete Stellung übergeht, wobei dieser Übergang durch eine Drehung um eine erste Achse (5) erfolgt, die senkrecht zur Flügelebene verläuft, wenn er sich in Mitnahmestellung befindet,
    und eine zweite Phase, in der der Flügel (2) von der halbentfalteten Stellung durch eine Drehung gemäß einer zweiten, parallel zur Flügelebene verlaufenden Achse (6) in die entfaltete Stellung übergeht.
  2. Entfaltungsvorrichtung gemäß dem Anspruch 1, dadurch gekennzeichnet, daß der Flügel (2) während der gesamten oder teilweisen ersten Phase der Entfaltungsbewegung durch einen Schalter betätigt wird.
  3. Entfaltungsvorrichtung gemäß den Ansprüchen 1 oder 2, dadurch gekennzeichnet, daß der Flügel (2) in Mitnahmestellung im Verhältnis zum Geschoß (1) durch ein Sperrorgan immobilisiert wird.
  4. Entfaltungsvorrichtung gemäß einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß sich der Flügel (2) in entfalteter Stellung unter der Einwirkung eines Steuermotors (14) um die erste Achse (5) herum drehen kann.
  5. Entfaltungsvorrichtung gemäß dem Anspruch 4, dadurch gekennzeichnet, daß der Steuermotor (14) der Schalter und/oder das Sperrorgan ist.
  6. Entfaltungsvorrichtung gemäß dem Anspruch 5, dadurch gekennzeichnet, daß der Flügel (2) mit einer Halterung (13) ein einziges Teil bildet, einer Halterung, die im Verhältnis zum Innenring (16) eines Wälzlagers immobilisiert ist, und daß der Außenring (15) dieses Wälzlagers im Verhältnis zum Geschoß (1) immobilisiert ist.
  7. Entfaltungsvorrichtung gemäß dem Anspruch 6, dadurch gekennzeichnet, daß der, Motor (14) im Verhältnis zum Geschoß (1) immobilisiert ist und mittels einem Kupplungsgelenk die Drehung der Halterung (13) steuert.
  8. Entfaltungsvorrichtung gemäß einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß der Flügel (2) während der zweiten Phase der Entfaltungsbewegung von aerodynamischen Kräften betätigt wird.
  9. Entfaltungsvorrichtung gemäß dem Anspruch 8, dadurch gekennzeichnet, daß der Flügel (2) einen Pion (22) besitzt, der während der ersten Phase der Entfaltungsbewegung in einer im Verhältnis zum Geschoß immobilisierten Rundrille (24) verläuft, wobei die zweite Phase mit dem Vorbeilaufen des Pions (22) an einer Aussparung (27) in dieser Rille (24) beginnt.
  10. Entfaltungsvorrichtung gemäß einem der Ansprüche 6 bis 9, dadurch gekennzeichnet, daß die Halterung (13) ein Schloß (23) besitzt, das den Flügel (2) in entfalteter Stellung im Verhältnis zur Halterung immobilisiert.
EP88402880A 1987-11-26 1988-11-16 Vorrichtung zum Ausspreizen der Leitflügel eines Geschosses Expired - Lifetime EP0318359B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8716389A FR2623898B1 (fr) 1987-11-26 1987-11-26 Dispositif de deploiement d'une ailette de projectile
FR8716389 1987-11-26

Publications (2)

Publication Number Publication Date
EP0318359A1 EP0318359A1 (de) 1989-05-31
EP0318359B1 true EP0318359B1 (de) 1992-06-17

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Application Number Title Priority Date Filing Date
EP88402880A Expired - Lifetime EP0318359B1 (de) 1987-11-26 1988-11-16 Vorrichtung zum Ausspreizen der Leitflügel eines Geschosses

Country Status (7)

Country Link
US (1) US5108051A (de)
EP (1) EP0318359B1 (de)
CA (1) CA1333027C (de)
DE (1) DE3872181T2 (de)
ES (1) ES2032045T3 (de)
FR (1) FR2623898B1 (de)
TR (1) TR23598A (de)

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CN106352746A (zh) * 2016-10-18 2017-01-25 湖北航天技术研究院总体设计所 一种折叠翼自动同步解锁驱动装置

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CA3041106C (en) 2009-09-09 2020-11-10 Aerovironment, Inc. Reinforced unmanned aerial vehicle launch tube
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CN116534299A (zh) 2014-03-13 2023-08-04 多韧系统有限责任公司 无人机配置和用于无人机内燃机的电池增大，以及相关的系统和方法
FR3039265B1 (fr) * 2015-07-21 2017-08-25 Dcns Projectile a ailettes de stabilisation de type couteau
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US9821909B2 (en) 2016-04-05 2017-11-21 Swift Engineering, Inc. Rotating wing assemblies for tailsitter aircraft
FR3054030B1 (fr) 2016-07-18 2018-08-24 Nexter Munitions Projectile comprenant un dispositif de deploiement d'une voilure ou ailette
CN107776870A (zh) * 2017-10-27 2018-03-09 成都云鼎智控科技有限公司 一种机翼折叠锁定组件及无人机
CN108100217A (zh) * 2017-12-29 2018-06-01 北京华信宇航科技有限公司 一种基于x翼布局的无人飞行器
US11300390B1 (en) * 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use
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CN112046731B (zh) * 2020-08-31 2022-06-10 中国电子科技集团公司第四十一研究所 一种x翼无人机尾翼折叠展开传动机构
CN113108652B (zh) * 2021-04-13 2022-09-27 哈尔滨工程大学 一种导弹舵面旋转折叠收放结构
CN114777574A (zh) * 2022-04-02 2022-07-22 合肥工业大学 一种折叠弹翼装置

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CN106352746A (zh) * 2016-10-18 2017-01-25 湖北航天技术研究院总体设计所 一种折叠翼自动同步解锁驱动装置

Also Published As

Publication number Publication date
FR2623898B1 (fr) 1990-03-23
DE3872181D1 (de) 1992-07-23
US5108051A (en) 1992-04-28
TR23598A (tr) 1990-04-24
DE3872181T2 (de) 1992-12-17
EP0318359A1 (de) 1989-05-31
ES2032045T3 (es) 1993-01-01
FR2623898A1 (fr) 1989-06-02
CA1333027C (fr) 1994-11-15

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