FR2590662A1 - DEVICE FOR BIAXIAL GUIDANCE OF A MISSILE - Google Patents

Abstract

With a device for guiding a missile, in particular a missile 1 can be moved around its pitch axis and its yaw axis. For this purpose, at the rear of the missile, a single control body 2 is mounted on a guide device 3 so that it can move radially and rotate. The guide device 3 moves the control body 2 first in one of the directions of movement, then then in the other direction of movement in the same plane of movement, so that finally, in the desired peripheral position, it protrudes eccentrically beyond the contour of missile 1. (CF DRAWING IN BOPI)

Description

Biaxial guidance device for a missile.

  The invention relates to a device for biaxially guiding a missile, in particular a submunition-releasing missile. German patent 30 24 908 discloses a guide device for directing the missile about an axis. It is anticipated that the surfaces of the trees

  can be adjusted by means of a motor. Such a structure

  ture is expensive. To allow guidance around two axes, it would take another motor with another pair

control surfaces.

  The object of the invention is to propose a device

  guide with which the flight position of the launch missile can be adjusted around its pitch axis

  and its yaw axis by means of a single control body.

  This object is achieved in accordance with the invention by mounting the missile on the rear of the missile, on a guiding device, a symmetrical control body with respect to the flight axis, the control body can be

  displaced axially (first direction of movement), radial-

  relative to the flight axis, by means of the guiding device, the control body can rotate, by means of the guiding device, around the flight axis or an axis parallel thereto (second direction of movement), and the guiding device moves with a motor the body

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  control, first in one of the directions of movement, then in the other direction, in a control position in which it exceeds the missile contour eccentrically with respect to the axis of flight. As long as the control body is in its central position, it does not influence the flight position. If displacement is desired, the control body is moved out to the appropriate location beyond the contour

  missile. The control body can come out at any location.

  the periphery of the missile. For that, only one

engine is enough.

  If the control body needs to be pulled out at a predetermined location from the periphery, or the control body is first pushed radially and it can be stopped in this position, for example by means of a stop; then, the engine continuing to operate causes a pivot along the periphery of the missile. Or the guide device is rotated first in the peripheral position of the control body necessary to influence the orientation, and then, after stopping the concentric rotation movement, the motor continuing to rotate leads to a radial displacement of the body control

  in its effective eccentric position.

  In a preferred embodiment of the invention, the control body is constituted by a truncated cone which tapers toward the missile and which, also in its central position, protrudes by its conical lateral surface beyond the contour of the missile. This truncated cone, in its central position, has a stabilizing effect on the position in flight. It brakes the flight speed of the

desired way.

  Other advantageous embodiments of the invention

  will appear in the following description of an example of

  embodiment shown schematically in the drawing, in which:

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  Figure 1 schematically shows a missile; Figure 2 is a view of the missile in the direction of the arrow II of Figure 1; and

  FIG. 3 is a perspective view of the

  positive missile guidance. Mounted on a dolly 1, in the rear, a control body 2 in the form of a truncated cone. Its small diameter corresponds to that of the fuselage of the missile; the control body in the form of a truncated cone 2 thus narrows towards the missile 1. In the central position (see FIG 1), it protrudes radially by its conical lateral surface, symmetrically with respect to the axis, beyond the fuselage

missile.

  The control body 2 can be moved radially with respect to the flight axis A in the direction of the arrow R, and, in the plane of its cross section, it is mounted on a guiding device 3 so as to

  be able to turn in the direction of the arrow D (see Fig. 2).

This is shown in fig. 3.

  On the missile 1 (see Fig. 3), a ring 4 is rotatably mounted about the flight axis A by means of a ball bearing 5. The ring 4 comprises a transverse bar 6. On this one is mounted

  a slider 7. This slider comprises two sliding blocks

  9, 10 connected by a rod 8. Each block 9, 10 is associated with a stop 11 on the ring 4. By means of two pressure springs 12, 13, the sliding blocks 9, rely on a portion of surface 14 of the bar

  6. The pressure springs 12, 13 hold-

  the slider 7 in the central position.

  The missile 1 is provided with a motor 15 for actuating the guiding device. Its motor shaft 16 freely crosses the transverse bar 6. At its end is fixed an eccentric drive member 17 which surrounds

  by a slot 18 a pin 19 disposed on the rod 8.

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  The control body 2 is attached to the blocks of

sliding 9 and 10.

  The operating mode of the device described is as follows: when the motor 15 rotates, the drive member 17 pivots and the slide blocks 9, 10 are moved on the crossbar 6 to the stop 11. The body of command 2 now protrudes radially beyond the missile contour (see Fig. 1 position shown in dashed lines, and Fig. 2). If the motor 15 continues to rotate, the ring 4 is forced to rotate with it. The control body 2 then rotates in the direction of the arrow D until it is at the desired location on the periphery of the missile. In this position the control body 2 is blocked by means not shown. The motor 15 can then be stopped. Depending on the asymmetric position of the control body, the missile 1 pivots about its pitch axis or yaw axis. If one removes the blocking of the control body 2, the pressure springs 12, 13 return the member 17 and with it the control body 2 in the central position or rest. The

  rotation performed does not need to be canceled.

  With regard to what has just been said, it starts from the fact that the pressure springs 12, 13 are small enough not to hinder the movement of the slider 7. However, it is also possible to calculate the pressure springs 12 and 13 with a force such that, when the motor 15 is actuated, it is firstly the ring 4 which is rotated. The control body 2 does not come out yet radially. Once the

  slide 7 is in the peripheral position

  desired ring, the ring 4 is then blocked by a

  sitif non represents, for example an electromechanical brake.

  With the motor 15 continuing to rotate, the sliding blocks 9 and 10 move due to the pivoting of the member 17,

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  thanks to which the control body 2 now goes out radially

up to the stop.

  The control of the motor 15 can be calculated so that it only rotates in one direction. But it can also be designed so that the motor 15 can rotate in both directions. In this last case,

  the angles of rotation necessary to reach the posi-

  the desired rotation are smaller, ie the position in flight can be

from the moment.

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Claims (8)

  Biaxial guidance device for a missile, characterized in that a control body (2) symmetrical with respect to the steering wheel (2) is mounted at the rear of the missile (1) on a guiding device (3). flight axis (A), the control body (2) can be displaced radially with respect to the flight axis (A) by means of the guide device (3), (first direction of movement R), the   control body (2) can be rotated by means of the arrangement   guide (3) about the flight axis (A) or an axis parallel thereto (second traveling direction D), and the guiding device (3) displaces with a motor (15) the control body (2), first in one of the directions of movement, and then in the other direction of   movement, to a command position in the-   which it exceeds, eccentrically with respect to the axis   flight (A), the outline of the missile (1).   2. Guiding device according to claim 1, characterized in that the guiding device (3) moves the control body (2) radially first to a stop (11) and then rotates it in the plane. of cross section.   3. Guiding device according to claim 1 or 2, characterized in that the control body (2) can be moved optionally in both directions from its central position, by means of the guiding device (3).   4. Guiding device according to one of the claims   tions, characterized in that the body of   Mande (2) can rotate in both directions by means of of the guiding device (3).   5. Guiding device according to one of the claims   characterized in that the guiding device (3) comprises a rotatably mounted ring (4) on which a slider (7) for the control body (2) can move radially.   6. Guiding device according to one of the   cations, characterized in that the motor (15)   acts on the slide (7) by means of a drive member   ment (17) rotatable about the flight axis (A).   7. Guiding device according to one of the   previous arrangements, characterized in that return springs (12, 13) are arranged between the slide (7). and the ring (4).   8. Guiding device according to one of the   prior art, characterized in that the control body is constituted by a truncated cone (2) which narrows towards the missile (1) and whose conical side surface protrudes, also in a central position, beyond the missile contour.