JPS61138096A - Guided missile - Google Patents

Abstract

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

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention is directed to a guided flying vehicle that expands the LT and increases the wing area in order to improve the maneuverability [Prior art] Fig. 3 shows , is an explanatory diagram showing an example of a conventional guided flying vehicle, in which (1) is a guided flying vehicle body, (2) is a steering wing, (3) is a stabilizing wing, (4) is a target tracking device, (5) is the target, ■ is the flying velocity vector of the guided flying body.

L is the force perpendicular to the flying direction, hereinafter referred to as lift force, θ is the angle between the reference axis 9 normal ground and the axis of the guided flight object, hereinafter referred to as attitude angle, α is the flying force The angle between the direction and the axis of the guided flight object, hereinafter referred to as the angle of attack.
σ is the target (5) seen from the guided flying object and the tracking device (4).
) is the angle formed with the direction of -hereinafter referred to as the swing angle. In order for the guided flying object to follow the movement of the target (4) and fly, a lift force is required to change the flight direction, and the most common method is to use an air blade for the lift force. It's a method.

That is, by moving the steering wheel
The target (5) needs to move at high speed, and in order to do so, the angle α must be increased. Alternatively, there is a way to increase the stability x(3).However.

As the angle of attack α increases, the generated lift force increases, but there is a limit to this, and once this limit is exceeded, the lift force does not increase any further but, on the contrary, decreases. Also, increase the angle of attack α (too much).

The swing angle σ becomes large, exceeding the limit of the swing angle of the tracking device (4), and there is a risk of losing sight of the target (5). If the stabilizer blade (3) is made too large, the launcher
9th voyage! It becomes difficult to install it on aircraft, ships, etc.

It also becomes difficult to handle. In particular, in the case of aircraft-mounted flight guides, if the stability The drawback was that the aircraft's stability was reduced.Therefore, when it was installed, the stabilizing wings (3) were folded to keep the two aircraft compact.

A deployable wing system was devised in which the aircraft could be deployed after launch, resulting in a large wing area and thus a large lift.

FIG. 4 is a cross-sectional view showing the structure of the deployable wing of a conventional inductive body, in which (a) shows the folded state and (b) shows the unfolded state. In the figure, (6) is the deployable wing, (7) is the shaft, (8) is the slider that slides on the shaft (7), and (9) is the deployable wing (6) and slider (8).
), links ° and u[ are coil springs that pull and move the slider (8), αυ is a locking mechanism that fixes the slider (8) when the deployable wing (6) is folded, and (13
is a wire that releases the locking mechanism, and a locking mechanism that fixes the deployable wings (6) when the α3fi is deployed.

When a conventional deployable wing type guidance body is mounted on a mother aircraft or launcher, the deployable wings (6) are folded as shown in Figure 4 (a) and fixed by a locking mechanism αD. After nine firings, the locking mechanism is released by pulling the wire αa after an appropriate time, and the slider (8) is pulled by the coil spring α and moves on the shaft (7). At this time.

The link (9) pushes the deployment wings (6) to deploy them.

Finally, as shown in FIG. 4(B), when the deployable wing (6) is deployed to a predetermined position, the locking mechanism 03 works to fix the deployable wing (6).

[Problems to be solved by the invention] In the conventional deployable wing-type guiding body as described above, a highly reliable drive force is used to overcome air resistance during flight and deploy the deployable wings (6). A source is necessary. As a driving source, in addition to the coil spring explained in Figure 4, gunpowder, "IIL motor, hydraulic pressure, pneumatic pressure, etc." can be considered, but all of them have complicated mechanisms, so reliability decreases and at the same time increases l quantity. There was a problem with that.

This invention was made in order to solve such problems, and aims to make it possible to expand A-Kin-Sho with a simple structure, improve reliability, and at the same time reduce the number of N-children.

[Means for Solving the Problem] The inductive body according to the present invention has a drag chute attached to the slider of the deployment mechanism, which can be discharged outside the aircraft after nine shots.

[Effect]

In this invention, the drag chute attached to the slider is ejected from the aircraft body after launch, and the driving force for moving the slider is obtained by the air resistance of the drag chute opened by the aerodynamic force during flight.

〔Example〕

FIG. 1 is a sectional view showing an embodiment of the present invention.
1) to (9) and αυ to α rise are exactly the same as the conventional inducible endothelial body shown in FIG. I is the case that stores the drag chute, α9 is the drag shoe), US is the wire connecting the drag chute and the slider (8), round η
is the wire that opens the drag chute storage case, u8
is a stopper that stops the slider (8) from moving. FIG. 2 is a cross-sectional view illustrating details of the slider (8) of the inductive body according to the present invention, where μ is a limit switch, CO is a spring that supports the limit switch in the neutral position, and υ is a spring that supports the limit switch in the neutral position. Removing wire ae is a stop wire.

When the inductive body configured as described above is mounted on the mother aircraft or launcher, the deployable wings (6) are folded as shown in Figure 1 (a) and fixed by the locking mechanism +111. After two shots, the locking mechanism αυ is released by pulling the wire az and the wire αn after an appropriate time, and at the same time, the drag chute storage case α4 is opened and the drag chute is discharged outside the aircraft. . The ejected drag chute opens due to the aerodynamic force while flying, generates resistance, and pulls and moves the slider (8) via the wire αe. At this time, the link (9) pushes the deployment wings (6) to deploy them. Finally, as shown in Figure 1 (
B) As shown in K, when the deployable JK f6) is deployed to a predetermined position, the locking mechanism u3 works to fix the deployable wing (6). In addition, as shown in Figure 2 (a), when the deployable wing (6) is not deployed to the predetermined position, the slider (8)
This is because the limit switch (19) and the stopper UIl are in a position where they do not come into contact with each other.

The limit switch (I9) is kept at the neutral position by the force of the spring 4. In this state, there is no force to pull out the wire D that prevents removal, and the wire C11 that prevents removal is fixing the wire Ull. drag shoot i
l! A force of 9 is transmitted to the slider (8). Expansion x (6
) is expanded to a predetermined position, the slider (8) moves to the position shown in Figure 2 (b), and the limit switch αt
is pushed by the stopper ua, and the stopper wire clυ connected to the limit switch is pulled out from the wire σe. When the wire I2υ is pulled out, the wire αe is separated from the slider (8) and pulled out by the air resistance of the drag chute 9. Furthermore, as shown in Figure 1 (c), drag chute (I9 and wire αe)
will be separated from the nine aircraft, leaving no harmful air resistance for further flight.

〔Effect of the invention〕

As explained above, this invention has a simple structure in which a drag chute is attached to a tied and guided flight body, which eliminates the need for a complicated drive source for deploying the deployable wing, and allows handling to be performed on each axis.

This has the effect of improving reliability and at the same time reducing the overall weight by the amount of the drive source.

[Brief explanation of the drawing]

Fig. 1 is a sectional view showing an embodiment of the present invention, Fig. 2 is a sectional view showing details of a part of the embodiment of the invention, and Fig. 3 is an example of a conventional fermentation flying object. The explanatory diagram, FIG. 4, is a sectional view showing an example of a conventional sabotage projectile. In the figure, (6) is the deployable wing, (7) is the shaft, and t
81 is a slider, (9) is a link, αυ is a locking mechanism,
(la is wire, u: 1l-j: lock mechanism, I is storage case, α9 is drag chute, αe is wire, fin is wire, aa is stopper, σIfi limit switch, (to) is spring, QD is removal It is a stop wire.The same reference numerals in each figure indicate the same or corresponding parts.

Claims (1)

[Claims] A deployment mechanism consisting of a deployment wing, a link for deploying the same, a slider, and a shaft, a locking device for fixing the deployment wing in a folded state, a wire for releasing this locking device, and a wire attached to the slider of the deployment mechanism through the wire. A drag chute and a case for storing the same, a wire for opening the storage case, a limit switch for separating the wire connecting the slider and the drag chute after wing deployment, a stopper for operating this at an appropriate time, and a stopper for setting the deployable wing in the deployed state. A guided flying object characterized by being equipped with a locking device for fixing the object.