JP2013228116A - Missile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a missile capable of stably separating an outer cylinder to open a head without using any pyrotechnic product by a simple configuration.SOLUTION: Before a mounting part 12 in a missile 1 is opened, steering is performed by using a front blade 8 (a). When a predetermined time for spraying a mounted article 10 comes, the binding of an outer cylinder 16 is released, and then the front blade 8 is rotated until its blade surface is made vertical with respect to the axial direction of the missile 1 (b). The mounting part 12 of the missile 1 is opened by separating the outer cylinder 16 from a body 4 by air resistance received by the front blade 8.

Description

  The present invention relates to a flying object that disperses an object mounted on the inside during flight, and more particularly, to a technique for separating an outer cylinder when the object is dispersed.

There is a flying body that discharges and disperses a mounted object to the outside during the flight in order to spray materials, small bombs, and the like in a target area (see Patent Document 1).
When the loaded object is in the body of the flying object, it is necessary to separate and open the outer cylinder of the flying object body when spraying the loaded object. For flying bodies such as rockets, the nose fairing divided into two parts is released using pyrotechnics and compression springs, and the tip of the outer cylinder is pushed out in the vertical direction of the flying body to separate it. There is a craniotomy method using a craniotomy method (see Patent Document 2).

JP 2009-276060 A Japanese Patent Laid-Open No. 11-20798

  However, the pyrotechnics and compression springs used to release the outer cylinder restraint and push out the outer cylinder reliably release the restraint and push out the outer cylinder reliably while flying at high speed. In addition, it is necessary to generate a force of a certain level or more, which causes problems such as a complicated structure, an increase in size and an increase in weight. In particular, when a pyrotechnic is used, there is a risk that the impact during the operation of the pyrotechnic will adversely affect the flying object and the load.

  The present invention has been made to solve such problems, and the object of the present invention is to provide a flying object capable of stably separating the outer cylinder with a simple configuration without using pyrotechnics. It is to provide.

  In order to achieve the above object, the flying body according to claim 1 is a flying body that disperses the loaded object mounted on the outside during the flight, and the fuselage on which the loaded object is mounted; An outer cylinder part separable from the outer shell of the outer shell, a restraining means for restraining the outer cylinder part and releasing the restraint at a predetermined time, and after the restraint by the restraining means is released, And aerodynamic force imparting means for separating the outer cylinder portion by applying aerodynamic force associated with flight to the front portion.

The flying body according to claim 2 is the flying object according to claim 1, wherein the aerodynamic force imparting means is a wing provided at a front portion of the outer cylindrical portion, and the wing surface is released after the restraint by the restraining means is released. It is characterized in that aerodynamic force associated with flight is given to the outer cylinder by intersecting with the direction.
According to a third aspect of the present invention, in the first aspect, the aerodynamic force imparting means communicates from an opening that opens in the flying direction at the head of the flying body to the inner surface of the outer cylinder front through the trunk. And an opening / closing means for opening and closing the opening. After the restraint by the restraining means is released, the opening is opened by the opening / closing means, and the opening is opened through the air introduction passage. It is characterized by applying aerodynamic force accompanying flight to the inner surface of the front part of the outer cylinder.

  In the flying body according to claim 4, in any one of claims 1 to 3, the restraining means engages with a claw portion formed at a front end of the outer cylinder portion to restrain the outer cylinder portion. It has a piece and is characterized in that the restraint is released by releasing the engagement between the engaging piece and the claw portion at the predetermined time.

According to the present invention using the above means, in the flying object that disperses the loaded object mounted inside during the flight, after the restraint of the outer cylinder by the restraining means is released, the flying object can fly to the front part of the outer cylinder. The outer cylinder is separated by applying the accompanying aerodynamic force.
Thus, by separating the outer cylinder using aerodynamic force, it is possible to open the flying object with an easy configuration without providing a large-scale device such as a pyrotechnic or a compression spring. In particular, by not using pyrotechnics, it is possible to reduce the influence on the flying object and the load when the head is opened.

1 is an overall configuration diagram of a flying object according to a first embodiment of the present invention. It is sectional drawing (a) (b) which follows the AA line of FIG. It is an expanded sectional view (a) and (b) which showed the restraint mechanism of the flying object concerning a 1st embodiment of the present invention. It is the top view (a) (b) which showed the concrete structure of the restraint mechanism of the flying body which concerns on 1st Embodiment of this invention. It is the top view (a) (b) which showed the modification of the restraint mechanism. It is a craniotomy operation | movement figure (a)-(c) of the mounting part in the flying body which concerns on 1st Embodiment of this invention. It is a whole block diagram of the flying body which concerns on 2nd Embodiment of this invention. It is a front view (a) (b) of a flying object concerning a 2nd embodiment of the present invention. It is the expanded sectional view (a) (b) which showed the specific structure of the opening mechanism of the flying body which concerns on 2nd Embodiment of this invention. It is an expanded sectional view (a) and (b) which showed the modification of the opening mechanism. It is the craniotomy operation | movement figure (a)-(c) of the mounting part in the flying body which concerns on 2nd Embodiment of this invention.

Hereinafter, embodiments of the present invention will be described with reference to the drawings.
First, the first embodiment will be described.
1 to 3, FIG. 1 is an overall configuration diagram of a flying object according to a first embodiment of the present invention, FIG. 2 is a cross-sectional view taken along line AA in FIG. 1, and FIG. Enlarged sectional views of the mechanism are shown, respectively, and will be described based on these drawings.

A flying body 1 shown in FIG. 1 includes a pointed head 2 and a cylindrical body 4, with four rear wings 6 on the rear outer periphery of the body 4 and two front wings 8 on the front outer periphery. Are provided.
The fuselage 4 of the flying body 1 has a mounting portion 12 on which a load 10 such as a material or a small bomb is mounted on the front portion, and a motor portion 14 on which a rocket motor is mounted on the rear side of the mounting portion 12. Is formed.

The mounting portion 12 has an outer shell formed by a pair of outer cylinders 16 (outer cylinder portions) that are divided into two in the direction perpendicular to the axial direction with the axial direction of the flying object 1 as a dividing plane except for the base portion 12a on the motor portion 14 side. It is configured.
Each of the front wings 8 is provided at the front portion of each outer cylinder 16, and more specifically, as shown in FIGS. 16 is connected to a rotating shaft 20 that extends through 16. The front wing 8 is moved from the state parallel to the axial direction of the flying object 1 shown in FIG. 2A by the operation of the actuator 18 under the control of a control device (not shown) mounted on the flying object 1. It can rotate to a direction perpendicular to the axial direction of the flying object 1 shown in FIG. Thus, the flying object 1 is steered by changing the angle of the front wing 8.

  Next, as shown in FIGS. 3A and 3B, the head 2 is provided with a restraining mechanism 22 (restraining means) capable of restraining the front end of the outer cylinder 16 and releasing the restraint at a predetermined time. Yes. As shown in FIG. 3A, the restraining mechanism 22 is configured such that the movable engagement piece 22 a engages with a claw portion 16 a that protrudes toward the inside of the body and toward the front at the front end of the outer cylinder 16. The outer cylinder 16 is restrained. It is assumed that the rear end of the outer cylinder 16 is fitted to the base 12a of the mounting portion 12. 3B, when the engagement between the engagement piece 22a and the claw portion 16a of the restraining mechanism 22 is released, the restraint of the outer cylinder 16 is released, and the outer cylinder 16 is outside the body 4. Can move freely.

  A more specific configuration of the restraining mechanism 22 is shown in FIG. As shown in FIGS. 4A and 4B, the engaging piece 22 a in the restraining mechanism 22 has a disc shape that is partially cut out in plan view, and the engaging piece 22 a has the restraining mechanism 22. It can be rotated around the central axis by an actuator (not shown). When the outer cylinder is restrained, the restraining mechanism 22 is arranged so that the side where the engagement piece 22a is not cut out straddles the head 2 and the outer cylinder 16, as shown in FIG. Thus, it engages with the claw portion 16a of the outer cylinder 16 as shown in FIG. On the other hand, when releasing the restraint, as shown in FIG. 4B, the engagement piece 22a is rotated around the central axis, and the notch surface is made to coincide with the boundary surface between the head 2 and the outer cylinder 16, As shown in FIG. 3B, the engagement with the claw portion 16a of the outer cylinder 16 is released to release the restraint.

  Note that the configuration of the restraining mechanism 22 is not limited to this. For example, as in a modification of the restraining mechanism shown in FIGS. 5A and 5B, a rod-like shape in which the engagement piece 22a ′ can slide in the front-rear direction. It does not matter even if it is the composition which made. As shown in FIG. 5A, the restraining mechanism 22 ′ of the modification is arranged so that the distal end portion of the engagement piece 22 a ′ straddles the head 2 and the outer cylinder 16 as shown in FIG. As a result, as shown in FIG. 3A, it engages with the claw portion 16a of the outer cylinder 16. On the other hand, when the restraint is released, as shown in FIG. 5B, the engagement piece 22a ′ slides forward by the action of the solenoid 22b ′ of the restraining mechanism 22 ′, so that the FIG. Thus, the engagement with the claw portion 16a of the outer cylinder 16 is released, and the restraint is released.

The flying body 1 in the first embodiment configured as described above separates the outer cylinder 16 at a predetermined time and opens the mounting portion 12 in order to spread the mounted object 10 in a predetermined region. Hereinafter, the opening operation of the mounting portion 12 in the flying object 1 will be described.
FIG. 6 shows a craniotomy operation diagram of the flying object mounting portion in the first embodiment, which will be described below with reference to FIG. FIG. 6 shows the mounting portion 12 in a sectional view for the sake of simplicity.

FIG. 6A is the same as the state of FIG. 1 and is a state before the flying object 1 is opened. In this state, the front wing 8 only rotates within a range necessary for steering the flying object 1 and does not rotate greatly.
When the predetermined time for spraying the load 10 is reached, the restraining mechanism 22 is released as described above under the control of the control device, and then, as shown in FIG. The blade surface is rotated until it becomes perpendicular to the axial direction of the flying object 1. When the front wing 8 is perpendicular to the axial direction, that is, the flying direction, the wing surface is greatly subjected to air resistance (aerodynamic force) associated with the flying of the flying object 1.

  Then, as shown in FIG. 6 (c), each outer cylinder 16 rotates outward with the rear end fitted as a fulcrum by the air resistance received by the front wing 8 provided at the front (white arrow). And begin to separate. The outer cylinder 16 that has started to be separated outside the body 4 receives air resistance on the inner surface of the outer cylinder 16 in addition to the front wing 8, and is further separated from the body 4. When the outer cylinder 16 is rotated more than a certain amount, the rear end is also disengaged, and the outer cylinder 16 is completely separated from the body 4. Thereafter, the load 10 is sprayed from the mounting portion 12 of the flying object 1.

As described above, in the flying object 1 according to the present embodiment, after the restraint mechanism 22 releases the restraint, the front wing 8 used for steering is rotated in the vertical direction so that the aerodynamic force is applied to the front portion of the outer cylinder 16. And the outer cylinder 16 can be separated by the aerodynamic force.
As described above, since the outer cylinder 16 can be separated by aerodynamic force, it is easy to use the front wing 8 used for steering without using a large-scale device such as a pyrotechnic or a compression spring. The mounting portion 12 can be opened stably with the configuration. In particular, in this embodiment, since the pyrotechnics are not used even when the restraining mechanism 22 is released, the influence on the flying object 1 and the load 10 at the time of the craniotomy can be reduced.

Next, a second embodiment will be described.
Referring to FIGS. 7 and 8, FIG. 7 shows an overall configuration diagram of a flying object according to the second embodiment of the present invention, and FIG. 8 shows a front view of the flying object. This will be explained based on this.
A flying body 30 shown in FIG. 7 includes a pointed head 32 and a cylindrical body 34, and four rear wings 36 are provided on the outer periphery of the rear part of the body 34. The flying body 30 of the second embodiment is steered by the rear wing 36.

The fuselage 34 of the flying body 30 is formed with a mounting portion 42 for mounting a load 40 such as a material or a small bomb at the front, and a motor portion 44 with a rocket motor mounted behind the mounting portion 42. Is formed.
The mounting portion 42, except for a part on the motor portion 44 side, has an outer shell constituted by a pair of outer cylinders 46 (outer cylinder portions) that are divided into two in the direction perpendicular to the axial direction with the axial direction of the flying body 30 as a dividing plane. Has been. The rear end of the outer cylinder 46 is fitted to the base 42a of the mounting portion 42, and the front end of the outer cylinder 46 is constrained by the same restraining mechanism as in the first embodiment, and will be described in detail. Is omitted.

  Opening mechanisms 50 (aerodynamic force imparting means) are provided at two locations on the head 32 of the flying body 30 corresponding to the outer cylinder 46. Specifically, as shown in FIG. 8A, the opening mechanism 50 is provided with a movable and substantially semicircular shutter 52 (opening / closing means) on one side and the other side of the outer periphery of the head 32. As shown in FIG. 8B, the shutter 52 is accommodated in the head 32 to open the opening 54 formed in the head 32. Since the opening 54 opens at the outer periphery of the head 32 having a pointed shape, the opening 54 opens in the flight direction.

  A specific configuration of the opening mechanism 50 is shown in FIG. As shown in FIGS. 9A and 9B, an air introduction passage 56 that communicates from the opening 54 to the inner surface of the front portion of the outer cylinder 46 is formed inside the head portion 32. A rack portion 52 a is formed on the inner surface of the lower portion of the shutter 52, and a gear 58 that meshes with the rack portion 52 a is provided inside the head portion 32. The opening mechanism 50 configured as described above is configured such that the opening portion 54 is closed by the shutter 52 illustrated in FIG. 9A by rotating the gear 58 by an actuator (not illustrated) included in the opening mechanism 50. As shown in (b), the shutter 52 can be housed in the head 32 and the opening 54 can be opened.

  The configuration of the opening mechanism 50 is not limited to this, and can slide into the head 32 at the lower end of the shutter 52 ′, for example, as in a modification of the opening mechanism shown in FIGS. A configuration in which a rod-like sliding portion 60 ′ is provided may also be used. The opening mechanism 50 ′ in the modified example slides the sliding portion 60 ′ into the head 32 by the action of the solenoid 62 ′ included in the opening mechanism 50 ′, so that the shutter 52 shown in FIG. From the state where the opening 54 is closed by ', the shutter 52' can be accommodated in the head 32 and the opening 54 can be opened as shown in FIG.

Also in the flying body 30 in the second embodiment configured as described above, the outer cylinder 46 is separated at a predetermined time to open the mounting portion 42 in order to disperse the mounted object 40 in a predetermined region. Hereinafter, the opening operation of the mounting portion 42 in the flying object 30 will be described.
FIG. 11 shows a craniotomy operation diagram of the flying object mounting portion in the second embodiment, which will be described below with reference to FIG. FIG. 11 is a sectional view showing the mounting portion 42 for the sake of simplicity.

FIG. 11A is the same as the state of FIG. 7 and is a state before the flying object 30 is opened. In this state, the shutter 52 of the opening mechanism 50 is closed and air is not introduced into the air introduction passage 56.
When the predetermined time for spraying the load 40 is reached, the restriction mechanism is released as in the first embodiment, and then the shutter 52 of the opening mechanism 50 is opened as shown in FIG. . When the shutter 52 is thus opened, air is introduced into the opening 54 that is open in the flight direction due to the ram pressure associated with the flight of the flying object 30 (white arrow), It passes through and is sent to the inner surface of the front portion of the outer cylinder 46.

  And as shown in FIG.11 (c), the outer cylinder 46 is pushed by an aerodynamic force from the inner surface of a front part (white arrow), and begins to separate by rotating outward with the rear end fitted as a fulcrum. . The outer cylinder 46 that has started to be separated from the body 34 receives air resistance on the inner surface of the outer cylinder 46 and is further separated from the body 34. When the outer cylinder 46 is rotated more than a certain amount, the rear end is also disengaged, and the outer cylinder 46 is completely separated from the body 34. Thereafter, the load 40 is sprayed from the mounting portion 42 of the flying object 30.

As described above, in the flying body 30 according to the present embodiment, after the restraint is released by the restraining mechanism, the shutter 52 is opened and air is introduced into the air introduction passage 56 from the opening 54 by the ram pressure. The outer cylinder 46 can be separated by applying aerodynamic force from the inner surface of the front portion.
As described above, since the outer cylinder 46 can be separated by aerodynamic force, it is a relatively easy configuration in which the opening portion 54 is simply opened by the shutter 52 without particularly providing a large-scale device such as a pyrotechnic or a compression spring. The outer cylinder 46 can be stably separated and the craniotomy can be performed. In particular, also in this embodiment, since the pyrotechnics are not used in the separation of the outer cylinder 46 and the release of the restraining mechanism, the influence on the flying object 30 and the load 40 can be reduced.

Although the description of the embodiment of the flying object according to the present invention is finished as above, the embodiment is not limited to the above embodiment.
For example, although the flying object 1 in each said embodiment is a rocket motor, a flying object is not restricted to this.
In the first embodiment, steering is performed by the front wing 8 and in the second embodiment by the rear wing 36. However, the steering means is not limited to this. For example, in the first embodiment, steering may be performed with the rear wing.

Moreover, in each said embodiment, although the outer cylinders 16 and 46 are divided into 2 in the mounting parts 12 and 42, what is necessary is just the outer cylinder divided | segmented into 2 or more divisions, according to the said division | segmentation number, An aerodynamic force imparting means such as an opening mechanism and a restraining mechanism may be provided.
In the first embodiment, the actuator 18 for rotating the front wing 8 is separated from the outer cylinder 16 when the head is opened. However, the actuator for rotating the front wing at the time of head opening is a fuselage. It does not matter even if it is configured to remain inside.

  In the first embodiment, when the head is opened, the front wing 8 is rotated until it is perpendicular to the flight direction in order to receive the maximum air resistance. What is necessary is just to rotate to the angle which can receive air resistance sufficient to isolate | separate an outer cylinder.

DESCRIPTION OF SYMBOLS 1,30 Flying object 2,32 Head 4,34 Body 8 Front wing 10,40 Mounted object 12,42 Mounted part 16,46 Outer cylinder (outer cylinder part)
16a Claw 18 Actuator 20 Rotating shaft 22, 22 'Restricting mechanism (restraining means)
22a, 22a 'engagement piece 50, 50' opening mechanism (pneumatic force applying means)
52, 52 'Shutter (opening / closing means)
52a Rack portion 54 Opening portion 56 Air introduction passage 58 Gear 60 'Sliding portion 22b', 62 'Solenoid

Claims (4)

A flying object that disperses the mounted items on the outside during flight,
A fuselage on which the load is mounted;
An outer cylinder part separable from the outer shell of the body;
A restraining means for restraining the outer cylinder portion and releasing the restraint at a predetermined time;
After the restraint by the restraining means is released, an aerodynamic force imparting means that separates the outer cylindrical portion by applying an aerodynamic force accompanying flight to the front portion of the outer cylindrical portion;
A flying object characterized by comprising:   The aerodynamic force imparting means is a wing provided at a front portion of the outer cylinder portion, and after the restraint by the restraining means is released, the wing surface crosses the flight direction to fly to the outer cylinder. The flying object according to claim 1, wherein the accompanying aerodynamic force is applied.   The aerodynamic force imparting means includes an air introduction passage communicating from an opening portion opened in the flying direction at a flying body head to the inner surface of the front portion of the outer cylinder through the fuselage, and opening and closing to open and close the opening portion. After the restraint by the restraining means is released, the opening is opened by the opening / closing means, and the air force accompanying the flight is applied to the inner surface of the front portion of the outer cylinder through the air introduction passage. The flying object according to claim 1, wherein the flying object is provided.   The restraining means has an engagement piece that restrains the outer cylinder part by engaging with a claw part formed at the front end of the outer cylinder part, and the engagement piece and the claw at the predetermined time. The flying object according to any one of claims 1 to 3, wherein the restraint is released by disengaging the part.

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