JPH0961099A - Warhead of airframe - Google Patents

Abstract

PROBLEM TO BE SOLVED: To surely orient the direction of scattering of shell splinters toward a target direction without necessitating a signal processing circuit, by a method wherein the center of mass of a rotating mechanism which is provided between the front and rear ends of a warhead shell and members located on the body axis of an airframe and holds the shell rotatably around the body axis is positioned between the body axis and the shell splinters. SOLUTION: A large number of shell splinters 4 are provided in one side part in a warhead shell 3 held in a fuselage of an airframe and an ignition mechanism 6 is provided in the other side part in the shell 3, while a bursting charge 5 is filled inside the shell 3. A rotating mechanism 7 which supports a warhead 2A rotatably is provided between the front and rear ends of the shell 3 and members located on the body axis 9 of the airframe and opposed to these end parts. Herein the position 8 of the center of mass of the warhead 2A is set between the body axis 9 and the shell splinters 4. When a warhead lock mechanism 17 is canceled, revolution of the warhead 2A is enabled. When the airframe turns round and lateral acceleration is given, the warhead 2A revolves so that the direction of scattering of the shell splinters be oriented toward the direction opposite to the direction of the acceleration.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a warhead of a flying vehicle that employs proportional navigation.

[0002]

2. Description of the Related Art FIG. 10 is an explanatory view of a conventional targeting mechanism in a warhead of a flying object. (A) is an explanatory view of a mutual positional relationship between the flying object and a target, and (b) is a drawing of the flying object. It is explanatory drawing which shows the cross-sectional view of a bullet head, and the flow of the signal from a seeker with respect to this.

In the figure, 31 is a flying object, 32 is a warhead, 33 is a seeker, 34 is a target, 35 is an explosive warhead piece, 36 is an ignition mechanism, 37 is a warhead explosive, and 38 is an ignition mechanism. It is an ignition control device that does.

In the conventional warhead shown in FIG. 10, as shown in FIG. 10B, ignition mechanisms 36 are provided at four locations around the warhead, and the seeker 33 of the flying body detects the target by tracking the target. Based on the information of the target direction, the ignition control device 38 selects the ignition mechanism 36 (No. 1 to No. 4) so that the scattering direction of the bullets 35 becomes the target direction, and sends an ignition signal to the ignition mechanism 36. I was trying to ignite.

[0005]

The conventional system has the following problems. (1) Since the direction of the target is determined from the target tracking information of the seeker, complicated signal processing is required, and an additional circuit is also required for selection / control of the ignition mechanism. (2) When the seeker lock is off or when the blinds are
Since the signal from the seeker is lost, it is necessary to take measures to maintain the target direction. Seeker lock-off occurs when the target signal reception state of the seeker becomes poor, and refers to the state in which the target tracking signal is interrupted, and blind is generally the seeker at the final stage when the missile approaches the target. Since the target signal received by the receiver is excessive and adversely affects the guidance system, the seeker function is stopped and the guidance state is fixed up to the opponent, which is the state where the target tracking of the seeker is not intentionally performed. (3) Since one of the plurality of ignition mechanisms is selected to determine the projectile scattering direction, an invalid projectile or explosive charge is generated in the scattering direction, and the scattering efficiency is reduced.

The present invention solves the above-mentioned drawbacks of the prior art in a vehicle using proportional navigation, does not require a signal processing circuit, and ensures that the projectile direction is directed toward the target direction. It is intended to provide warheads.

[0007]

SUMMARY OF THE INVENTION The present invention solves the above problems and relates to a warhead of a flying vehicle having the following features. (1) Outer shell to be housed in the fuselage body, a large number of bullets provided on one side of the outer shell, ignition mechanism provided on the other side of the outer shell, and outer shell An explosive filled inside the outer shell and a front end and a rear end of the outer shell, and the outer shell provided between the front end and the rear end of the outer shell and a member on the fuselage axis facing the above portion, and rotatably holding the outer shell around the fuselage axis It was equipped with a rotating mechanism that operates so that its center of mass is located between the body axis and the bullet. (2) Outer shell that is housed in the fuselage body at a distance from the inner wall of the fuselage, a large number of bullets provided at the front end of the outer shell, and the rear end of the outer shell The ignition mechanism provided in the outer shell, the explosive charged in the outer shell, and the outer shell provided between the rear end of the outer shell and a member on the fuselage axis of the aircraft facing the rear end. It was equipped with a joint mechanism that holds the so that it can be tilted in any direction with respect to the machine axis.

[0008]

1 is a vertical sectional view of a flying body according to a first embodiment of the present invention. In the figure, 1 is a flying body and 2A is a warhead. This warhead 2A is a rotary directional warhead.

2A and 2B are cross-sectional views of the fuselage of the flying body in the vicinity of the warhead 2A in the above embodiment, FIG. 2A being a horizontal cross-sectional view and FIG. In the figure, 3 is a warhead outer shell, 4 is a bullet piece, 5 is an explosive charge, 6 is an ignition mechanism, 7 is a rotating mechanism that rotatably supports the warhead 3, 8 is a position of the center of mass of the warhead 3, and 9 is a body. It is the axis and the centerline of the rotation. Further, 17 is a solenoid actuator type warhead locking mechanism, and 18 is a safety detonator. The warhead 2A is composed of parts 3, 4, 5, 6, and 7.

In this embodiment, the warhead lock mechanism 1
When 7 is released, the warhead 2A can rotate.
When the flying body turns and a lateral acceleration is applied, due to the mutual relationship between the body axis 9 and the position of the center of mass of the warhead with respect to this, the warhead rotates so that the flying direction of the bullet is in the direction opposite to the acceleration direction.

A flying body using proportional navigation has a characteristic of turning in the direction opposite to the target in the vicinity of the enemy with the target. Considering the projection on the plane of the cross section of the flying object, the acceleration is applied in the direction opposite to the target direction. When explosive ignition is performed by the ignition mechanism 6 based on an ignition signal output from the safety detonator 18 when the target encounters the enemy, the bullet 4 is ejected in the target direction.

FIG. 3 is a vertical sectional view of a flying body according to a second embodiment of the present invention. In the figure, 1 is a flying body and 2B is a warhead. This warhead 2B is a retractable directional warhead.

4A and 4B are vertical sectional views of the fuselage body of the flying body in the vicinity of the warhead 2B in the above embodiment. FIG. 4A shows the fixed position, and FIG. 4B shows the warhead tilted to one side. In the figure, 3 is a warhead shell, 4 is a bullet piece, 5 is an explosive charge, 6 is an ignition mechanism, 9 is a fuselage axis, 10 is a joint mechanism capable of tilting the warhead with respect to the same axis, 17 Is a warhead lock mechanism, and 18 is a safety detonator. Warhead 2B
Is composed of parts 3, 4, 5, 6, and 10.

In the present embodiment, the warhead lock mechanism 1
When 7 is released, the warhead 2B becomes a joint mechanism 1 at the rear end.
It becomes possible to swing around 0. When the flying body turns and a lateral acceleration is applied, the warhead 2B tilts with respect to the fuselage axis 9 so that the projectile scattering direction faces the direction opposite to the acceleration direction.

In a spacecraft using proportional navigation,
As described above, in the vicinity of the enemy with the target, it has a characteristic of turning in the direction opposite to the target. Considering the projection on the plane of the cross section of the flying object, the acceleration is applied in the direction opposite to the target direction. The ignition mechanism 6 is based on an ignition signal output from the safety detonator 18 when a target encounters the enemy.
When the explosive ignition is performed by, the bullet 4 is ejected in the target direction.

FIG. 5 is a diagram showing an example of calculation of the directivity angle limited range of the retractable directional warhead 2B. The directivity angle θ of the warhead is
Although limited by the length L and radius d of the warhead shell 3, the shape of the warhead shell is within the range A in the figure from the number of bullet pieces required for target destruction, the amount of explosive charge, and the directivity angle requirement for each target to be dealt with. By setting, the warhead of this embodiment can be realized so as to have a directivity angle necessary for destroying the target.

The flying body described in each of the above-mentioned embodiments uses proportional navigation as a guidance system. FIG. 6 is an explanatory diagram of proportional navigation. In the figure, a deviation from the enemy path occurs due to a change in the direction of the target 19 with respect to the flying object 1, that is, the line-of-sight angle (σ). Therefore, in order to place the flying body on a new enemy path, the path angular velocity dγ / which is proportional to the change rate dσ / dt of the visual line angle.
Rotate the flying body to generate dt. This navigation is proportional navigation. That is, when N is a navigation constant, the flight route is controlled by dγ / dt = N · dσ / dt.

In proportional navigation, the vehicle is not guided to the target, but to the predicted enemies. This predictive meeting point is constantly changing due to changes in the speed of the flying object and the target, activation of the target, etc. The flying object is required due to the seeker's boa sight error (deviation between the seeing direction of the seeker and the target direction). Calculates the correct turning acceleration and changes the route. Since the flying object needs an angle of attack to generate the turning acceleration, the aircraft is tilted in the turning direction with respect to the speed direction. As a result, the direction of the target and the direction of turning acceleration based on the aircraft axis of the flying body are opposite. As a condition of application, the present invention is applied to a flying object that turns by aerodynamic force, and cannot be applied to a flying object (type having a thruster at the center of gravity of the body) capable of changing the route regardless of the attitude of the aircraft.

The present invention can be applied only to a flying object using proportional navigation, and in the vicinity of the enemy with the target, the flying object is in a direction opposite to the direction of the target with respect to the axis of the flying vehicle. By utilizing the characteristic that the turning acceleration is generated, the means for changing the direction of the warhead by the force acting on the warhead by the generation of the turning acceleration and directing the direction of the bullet piece toward the target is adopted. This makes it unnecessary to determine the target direction based on an external signal, and the warhead itself can be oriented in the target direction to improve the scattering efficiency.

FIG. 7 is an explanatory view of the relationship between the direction of the target seen from the flying object in the vicinity of the enemy and the direction of turning acceleration applied to the flying object. FIG. 7A shows the positional relationship between the flying object and the target. FIG. 1B is a rear view of the flying body. In the figure, 1 is a flying object, 19 is a target, 16 is a target direction on a plane orthogonal to the aircraft axis, and 15 is a turning acceleration direction. In FIG. 7A, the target direction 1
6 and the turning acceleration direction 15 are opposite directions. Figure 7
In (b), the target direction angle measured from the yaw axis is φT,
If the turning acceleration direction is φG, the relationship in the opposite direction is φ
T = φG ± 180 °.

FIG. 8 is a diagram showing a time history of the target direction and the turning acceleration direction obtained by carrying out the flight guidance simulation. (A) is a positional relationship diagram between a flying object and a target, and (b) is a time history diagram in each of the above directions. In the figure, the target moves at Mach 1. The projectile has reached Mach 3 after launch. It is assumed that, 5 seconds after the launch of the projectile, the target that has detected the approach of the projectile makes a 9G turn and starts an avoidance motion. This is a simulation assuming that the flying body also makes a turning motion in response to this. In this simulation as well, it was confirmed that the difference between the target direction φT and the turning acceleration direction φG on the plane orthogonal to the machine axis was always kept at 180 degrees before and after the start of the target turning. The rationality of changing the direction was confirmed.

FIG. 9 is a diagram showing an operation sequence (representative example) of the close fuse and the warhead that lead to the destruction of the target. The projectile is guided to the target, and the predicted enemy time is 0.5se
c Before the command of the missile computer is activated, the proximity fuse is activated to output the target detection beam, and the warhead lock mechanism is released to enable the warhead to rotate (or tilt). The force acting on the warhead generated by the turning of the flying body changes the direction of the warhead to the target direction. Even if the movement of the target changes during this period, the warhead follows well and holds the target within the range of the projectile scattering angle. When the proximity fuze detects the target, the ignition signal is output from the proximity fuze to the warhead after the warhead detonation delay time has elapsed, and the warhead detonates.
This warhead detonation delay time controls the firing time of the warhead in order to hit the target efficiently with the projectile, and is usually set in the range of 0 to several msec depending on the target type and the enemy situation. It The fragments released by the detonation of the warhead hit the target, and its energy can destroy the target.

[0023]

In the warhead of the flying object of the present invention,
Outer shell contained in the fuselage fuselage, a large number of bullets provided on one side of the outer shell, ignition mechanism provided on the other side of the outer shell, and filling of the outer shell And a rotating mechanism that is provided between the front and rear ends of the outer shell and the members on the fuselage axis of the flying body that face these portions, and that holds the outer shell rotatably around the fuselage axis. The outer shell, which is configured so that its center of mass is located between the body axis and the bullet piece, or is housed in the flight fuselage body at a distance from the inner wall of the fuselage, A large number of bullets provided at the front end of the inner shell, an ignition mechanism provided at the rear end of the outer shell,
An explosive filled in the outer shell, and the outer shell provided between the rear end of the outer shell and a member on the fuselage axis facing the rear end of the outer shell in an arbitrary direction with respect to the fuselage axis. Since it is equipped with a joint mechanism that holds it so that it can be tilted, the direction of the warhead can be changed by the turning acceleration, the signal processing circuit for the target direction is not required, and the projectile direction can be reliably targeted with a simple structure. Can be turned.

[Brief description of drawings]

FIG. 1 is a vertical sectional view of a flying body according to a first embodiment of the present invention.

2A and 2B are cross-sectional views of a fuselage fuselage in the vicinity of a warhead in the above embodiment, where FIG. 2A is a horizontal sectional view and FIG. 2B is a vertical sectional view.

FIG. 3 is a vertical sectional view of a flying body according to a second embodiment of the present invention.

FIG. 4 is a vertical cross-sectional view of a fuselage body of a flying body near a warhead in the above-described embodiment, (a) being a warhead fixing position, and (b).
Shows the warhead tilted to one side.

FIG. 5 is a diagram showing a calculation example of a directivity angle limit range of the warhead shell of the above embodiment.

FIG. 6 is an explanatory diagram of proportional navigation of a flying object.

FIG. 7 is an explanatory diagram of a relationship between a target direction viewed from a flying object in the vicinity of the enemy and a turning acceleration applied to the flying object, and FIG. 7A is a diagram showing a positional relationship between the flying object and the target; (B) is a rear view of the flying object.

8A and 8B are diagrams showing a time history of a target direction and a turning acceleration direction obtained by carrying out a flight guidance simulation, in which FIG. 8A is a positional relationship diagram between the flight object and the target, and FIG. It is a time history diagram of each said direction.

FIG. 9 is a diagram showing an operation sequence (representative example) of a close fuse and a warhead that lead to target destruction.

FIG. 10 is an explanatory diagram of a target orientation mechanism in a conventional projectile warhead, (a) is an explanatory diagram of a mutual positional relationship between the projectile and a target, and (b) is a crossing of the projectile warhead. Explanatory drawing which shows the flow of the signal from a seeker with respect to a floor plan and this.

[Explanation of symbols]

1 Flying Body 2A Warhead (Rotary Directional Warhead) 2B Warhead (Retractable Directional Warhead) 3 Warhead Outer Shell 4 Bullet Piece 5 Explosive Charge 6 Ignition Mechanism 7 Rotation Mechanism 8 Mass Center Position 9 Aircraft Axis 10 Joint Mechanism 15 Turning Acceleration direction (on plane orthogonal to machine axis) 16 Target direction (on plane orthogonal to machine axis) 17 Warhead locking mechanism 18 Safe detonator 19 Target A Achievable warhead length and warhead radius in the second embodiment Range φG Turning acceleration direction angle φT Target direction angle

Claims (2)

[Claims] 1. An outer shell housed in a fuselage body, a large number of bullets provided on one side of the outer shell, an ignition mechanism provided on the other side of the outer shell, It is provided between the explosive charged in the outer shell and the front and rear ends of the outer shell and the member on the body axis of the flying body facing these parts, and the outer shell can be rotated around the body axis. A warhead of a flying vehicle, characterized by having a rotation mechanism for holding it at its center of mass located between the body axis and the bullet. 2. An outer shell, which is housed in the flying fuselage at a distance from an inner wall of the fuselage, a large number of bullets provided at a front end portion of the outer shell, and inside the outer shell. The ignition mechanism provided at the rear end, the explosive charged in the outer shell, and the rear end of the outer shell provided between the rear end of the outer shell and a member on the fuselage shaft of the aircraft facing the rear end, A warhead for a flying vehicle, which is equipped with a joint mechanism that holds the outer shell so that it can be tilted in any direction with respect to the fuselage axis.