JPS6371499A - Steering gear for guided missile - Google Patents

Abstract

(57) [Abstract] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a steering device for a guided flying object such as a missile.

[Prior Art] Conventionally, motors (servo motors, etc.) and electromagnetic solenoids have been used as steering devices for transparent flying objects. That is,
For example, as shown in FIG. 8, these are mounted on a guided flying object 11, and the steering blades 12 are mechanically driven and redirected from these drive sources (4) around the axis m to steer and guide the flying object. It is something to do.

[Problems to be Solved by the Invention] Incidentally, it is desirable that the guided flying object itself be compact and lightweight. However, there are problems in that mounting these steering devices requires extra space, requires a complicated arrangement, or increases weight.

The present invention has been made with attention to such problems, and an object of the present invention is to realize a steering device for a guided flying vehicle that has a simple structure, is smaller in size, and is lighter in weight.

Means for Solving the Problems" In order to achieve the object, the present invention takes the following means. That is, a steering blade including an elastically deformable blade core and piezoelectric bodies attached to both sides of the blade core is provided, and different displacements are applied to the piezoelectric bodies on both sides of the steering blade. Accordingly, the steering blade is curved.

[Operation] With such a method, by applying different displacements to the piezoelectric bodies on both sides of the steering blade, the entire blade including the blade core is elastically deformed by the stress, and this is used as the steering angle displacement. be able to.

[Example] Hereinafter, one embodiment of the present invention will be described with reference to the drawings.

FIG. 1 shows a cross section of the steering device for a guided flying vehicle according to this embodiment. A plurality of piezoelectric bodies 3 are attached symmetrically and together form the central part of the wing 1.

Further, at both ends of the piezoelectric body 3, a leading edge part 5 and a trailing edge part 6 are fixed to the blade core 2 with these parts sandwiched therebetween. still,
A stretchable film 7 is attached to the entire surface of the wing 1 constructed in this manner.

By the way, each of the piezoelectric bodies 3 is constructed by laminating a large number of thin plate-shaped piezoelectric elements 3a with electrodes 3b in between, as shown in FIG. Note that FIG. 2 is an enlarged view of a part of the piezoelectric body 3 attached to the two wing parts.

FIG. 3 shows a further enlarged view of a part of this piezoelectric body 3. As shown in the figure, the piezoelectric element 3a has an effect of elongating in the vertical direction with respect to the electrode 3b (hereinafter referred to as the vertical effect) as shown in FIG. ), it produces the effect of shortening in the vertical direction (hereinafter referred to as the horizontal effect) as shown in FIG. For convenience'-1 As shown in Fig. 4, when a positive voltage is applied to the front F side of the piezoelectric element 3a and a negative voltage is applied to the back side 8 sides, a longitudinal effect occurs, and in the opposite case, that is, a negative voltage is applied to the front F side. , it is assumed that a transverse effect occurs when a positive voltage is applied to the eight back sides.

That is, as is clear from FIG. 3, the arrangement of the piezoelectric cables 3a described above is such that the piezoelectric elements 3a are alternately turned upside down with the electrode 3b in between so that the F side and the F side and the 8th side and the 8th side face each other. Furthermore, in order to apply the same voltage to the front and back sides of each piezoelectric element 3a, the electrodes 3b that contact the F side are all connected to the same power terminal p, and the 8 sides The electrodes 3b that come into contact with are all connected to the same power supply terminal q. As a result, when the power is turned on, each piezoelectric element 3a exhibits the same type of effect at the same time, and the piezoelectric body 3 as a whole can be displaced in the vertical direction and in the lateral direction.

On the other hand, FIG. 5 is an enlarged view of a part of the piezoelectric body 3 disposed in the upper wing, but as can be seen from the comparison with FIG. 3 which shows the upper wing, Electrodes 3b that are in contact with the front F surface and the back 8 surface of the piezoelectric element 3a are connected to opposite terminals in both figures.

As a result, when a positive voltage is applied to the terminal p and a negative voltage is applied to the terminal q, for example, a vertical effect appears in the piezoelectric element 3a of FIG. 3, whereas a horizontal effect appears in the piezoelectric element 3a of FIG. 5.

In this way, by applying opposite displacements to the piezoelectric bodies 3 of the upper wing section and the upper wing section across the wing core 2, this can be used as a steering angle displacement as explained below. be.

Now, if a vertical effect occurs in the piezoelectric element 3a of the wing section, =
4 - Assume that a lateral effect occurs on that of the upper wing. Then, in the wing part, the stress generated by this acts on the front and rear edges 5.6, and the upper wing side end surfaces 5a, 6a of the edges are moved as seen in the direction of the arrow 1 in FIG.
Pressed in the direction. On the other hand, the upper wing portion absorbs this pressing force by shrinking in the direction of the arrow (■) in the figure. As a result, the blade 1 as a whole is curved together with the blade core 2 so that the upper blade side in the figure has a convex shape. That is, by utilizing this warpage as a steering angle displacement, it is possible to function as a steering means with the two blades serving as a negative pressure surface and the upper blade serving as a positive pressure surface.

Conversely, if the piezoelectric element in the upper wing section exerts a transverse effect and that in the upper wing section exhibits a longitudinal effect, stress in the opposite direction to that in the case described above is generated in the upper wing and the upper wing, and the above-mentioned wing 1 The upper wing side in the figure can be curved to form a concave shape to function as a steering means with the two wings serving as a pressure surface and the upper wing serving as a negative pressure surface.

Regarding these operations, if the magnitude and polarity of the applied voltage is appropriately controlled to the plurality of attached wings, it is possible to arbitrarily select the direction and magnitude of the steering of the entire flying object. It is possible to realize a steering device. In addition, the steering device according to this embodiment can be constructed to be lightweight and compact, and furthermore, since electrodes are arranged opposite to each other for each piezoelectric element, it can operate satisfactorily even at a low voltage of about 100 V or less, and can obtain a large displacement. It has the advantage of being able to Furthermore, since the piezoelectric element is characterized by requiring only a small amount of current, the power consumption is small and the on-board power supply can also be small.

It goes without saying that this will lead to fewer failures and improved reliability.

In addition to the above configuration, the present invention is constructed by laminating thin plate-like piezoelectric elements 8 parallel to the blade core 9 surface as shown in FIG. Front and rear edges 10
You may also press the button. In addition, various modifications can be made to the structure of the piezoelectric body, etc., without departing from the spirit of the present invention.

[Effects of the Invention] With the above-described configuration, the present invention can provide a steering device for a guided flying object that has a simple structure and is reduced in size and weight.

[Brief explanation of the drawing]

Figures 1 to 6 show one embodiment of the present invention, Figure 1 is a partially cutaway perspective view showing the inside, and Figure 2 is an enlarged view of the piezoelectric body attached to one side of the wing. Figure 3 is a partially enlarged view of the same piezoelectric body, Figure 4 is an explanatory diagram of the action of the piezoelectric element, Figure 5 is a partially enlarged view of the piezoelectric body attached to the other side of the blade, and Figure 6 is a partially enlarged view of the piezoelectric body. FIG. 4 is an explanatory diagram of the operation of the steering blade. Moreover, FIG. 7 is a sectional view showing another embodiment. FIG. 8 is a perspective view showing a conventional example.

Claims (1)

[Claims] A steering blade including an elastically deformable blade core and a piezoelectric body attached to both sides of the blade core is provided, and the steering blade is manufactured by applying different displacements to the piezoelectric body on both sides of the steering blade. A steering device for a guided flying object, characterized in that the steering device is curved.