JPH04297796A - Guided missile - Google Patents

Abstract

PURPOSE:To improve a follow-up performance against a super-high speed small- sized target. CONSTITUTION:Composing elements of the prior art device are arranged in their opposite direction except a propulsion device 24, and further there are provided an operation period discriminating circuit 26 for use in discriminating in response to a relative distance for the prior art device, an accelerating and propulsion auxiliary propulsion device 29, a propulsion device separating mechanism 30 for separating the propulsion device or the like, a propulsion device separation sensing circuit 31 for use in sensing the separation, a missile alignment delay circuit 32 for sensing an alignment of the missile and outputting a control signal and an operation starting instruction circuit 33 for instructing a starting of function for use in locking-on on a target 1. A relative speed with respect to the target is controlled to cause a timing for triggering the missile explosive to be better and then a performance for shooting down the target is improved.

Description

[Detailed description of the invention]

0001

[Industrial Application Field] This invention extracts a target signal from the reflected wave from the target, locks on to the target, captures the target, and
This relates to a guided flying vehicle that tracks a target based on command signals from the launcher until it can track the target, and after locking onto the target, extracts the target signal from the reflected waves from the target to capture and track the target.

0002

[Prior Art] FIG. 11 is a diagram showing a conventional guided flying vehicle of this type. In the figure, M is a guided flying vehicle, and 1
is the target to be captured and tracked by the guided flying vehicle, 2 is the transmitted wave irradiated to target 1 from the antenna 6, 3 is the reflected wave from target 1, and 4 is the transmission signal of the transmitted wave 2 that is irradiated to target 1. A transmitter 5 supplies the transmission signal generated by the transmitter 4 to the antenna 6 but not to the receiver 7, and supplies the signal received by the antenna 6 to the receiver 7 but not to the transmitter 4. 6 is an antenna that irradiates the transmission signal generated by the transmitter 4 to the target 1 and receives the reflected wave 3 from the target 1; 7 is the reception signal that is received by the antenna 6 and supplied via the circulator 5; a receiving device that generates a target lock-on signal and a target signal after target lock-on;
Reference numeral 8 indicates an inertial navigation device that generates position and speed information of the guided flying object after it has been launched from the launcher 12, and 9 indicates a target signal output from the receiver 7 or a target command signal output from the command receiver 15, and an inertial navigation system. An error signal generator 10 extracts an error signal from the position/velocity information output from the device 8;
11 is a steering device that steers the flight path of the guided flying object M in the direction of the meeting point with the target 1 using the error signal output from the error signal generator 9; 12 is the guided flying object; At the same time as launching the body M, the guided missile M locks on to the target 1.
13 is a command signal emitted from the launcher 12, and 14 is a command that receives the command signal 13 emitted from the launcher 12. A receiving antenna 15 indicates a command signal 13 received by the command receiving antenna 14.
19 is a proximity fuse that generates a proximity detonation pulse when the guided projectile M passes near target 1; 20 is a proximity fuse that generates a proximity detonation pulse when the guided projectile M directly hits target 1; Arrival tube that generates pulses, 21
22 is a detonation signal generation circuit 2 which generates a detonation signal when the proximity detonation pulse output from the proximity fuse 19 or the arrival detonation pulse output from the arrival tube 20 is input;
Ammunition that explodes with a detonation signal of output 1 and causes great damage to target 1; 23 is a power source that supplies the necessary power to each component of guided missile M; 24 is a power source that provides thrust to guided missile M; It is a propulsion device that gives

Next, the operation will be explained. During initial and intermediate guidance after launch from the launcher 12, a command signal 13 is irradiated to the guided flying object M. Guided projectile M is launcher 12
The guided missile M flies in the direction of the rendezvous point with the target 1 by the command signal 13 emitted from the target 1, and at the same time directs the antenna 6 toward the target 1, and after locking on to the target 1 and transitioning to the final guidance, the guided missile M: An error signal is extracted from the reflected wave 3 of the target 1 received by the antenna 6, self-guided toward the meeting point with the target 1, and finally when the guided flying object M passes near the target 1, or , When it hits directly, it detonates ammunition 22, causing great damage to target 1 and shooting it down. Note that the components are arranged in approximately order from the tip in the propulsion direction, from the antenna 6 to the propulsion device.

0004

[Problem to be Solved by the Invention] Conventional guided missiles are constructed as described above, so the higher the target speed, the more the timing delay in detonating the ammunition becomes a problem.
There was a drawback in that when a target exceeds a predetermined relative speed, the guided projectile M becomes powerless because the hardware causes the detonation to occur after the target has passed. Particularly in recent years, there has been a strong desire to improve the ability of guided aircraft to shoot down small, ultra-high-speed targets, and the above-mentioned drawbacks have become an important issue.

The present invention was made to solve the above-mentioned problems, and aims to provide a device that does not disable the target.

[0006]

[Means for Solving the Problems] A guided flying object according to the first aspect of the present invention propels components from the antenna to the propulsion device, which were conventionally attached approximately in order from the tip in the propulsion direction. At the same time, it calculates the relative distance to the target and determines whether it is within a predetermined relative distance, outputs a low level signal when it is beyond a predetermined relative distance, and at the same time, it calculates the relative distance to the target and determines whether it is within a predetermined relative distance. Then, there is a means for outputting a high level signal, a means for auxiliary propulsion that accelerates the guided spacecraft when the output of the means becomes a high level signal, and a means for auxiliary propulsion and propulsion after the guided spacecraft accelerates. means for disconnecting the device; means for detecting that the propulsion device has been disconnected and outputting a disconnection signal; and means for outputting a start command signal after the aircraft has stabilized after being disconnected;
The apparatus is equipped with means for starting the operation of a transmitter, receiver, antenna, etc. in response to a start command signal.

[0007] A guided flying object according to a second invention of the present invention is the same as that of the first invention, and a means for causing even the slightest damage to the target by changing the direction of separation of the propulsion device in the direction of the target based on the error signal. It is equipped with the following.

[0008] A guided flying object according to a third aspect of the present invention is the same as that of the first aspect, in order to detach the propulsion device in a direction other than the target direction based on an error signal, and to lock on to the target as quickly as possible. It is equipped with the means of

The guided flying object according to the fourth invention of the present invention is different from the first invention in that it outputs a high level signal when the relative speed is faster than a predetermined speed according to the speed information, and outputs a low level signal when it is slower. and means for setting the direction of separation of the propulsion device as a target when a high-level signal is input, and means for setting the direction of separation of the propulsion device outside the target direction when a low-level signal is input.

A guided flying vehicle according to a fifth aspect of the present invention is the same as the guided flying vehicle according to the fourth aspect of the present invention, which is provided with means for controlling the propulsive force of the auxiliary propulsion device in accordance with the relative speed.

[0011] A guided flying object according to a sixth aspect of the present invention is provided with a means for determining whether or not it will directly hit a target based on an error signal, and a guided flying object when it is determined that it will hit a target directly. It is equipped with means for attenuating the speed of the projectile and increasing its relative speed to the target.

0012

[Operation] The first invention of the present invention is that, in the early and middle stages, the target is flown in the same direction as the target flight direction according to the command signal from the launcher on the predicted flight trajectory of the target, and the relative distance is within a predetermined distance. Once inside, the propulsion device is disconnected, the antenna is pointed in the direction of the target, and after locking on to the target, it is autonomously guided toward the meeting point with the target, and finally when the target passes near the guided missile (if it hits directly, there will be no problem) (No points) Since the relative speed can be significantly reduced compared to conventional methods, the timing of the detonation can be determined, preventing the guided projectile from becoming powerless.

[0013] In addition to the effect of the first invention, the second invention of the present invention makes it possible to cause damage to the target even slightly by the separated propulsion device by separating the propulsion device in the direction of the target. to control guided projectiles.

In addition to the effects of the first invention, the third aspect of the present invention is to separate the propulsion device in a direction other than the target direction so that it does not become an obstacle when locking on to the target. Control the guided projectile so that it locks on as quickly as possible.

In addition to the effect of the first invention, the fourth aspect of the present invention is to change the direction of detachment of the propulsion device in order to cause as much damage as possible to the target when the relative speed with the target is high. If the target direction is slow, the guided missile is controlled so that the propulsion device is separated from the target direction so that it can lock on to the target as quickly as possible.

[0016] In addition to the effects of the fourth invention, the fifth aspect of the present invention is to control the relative speed of the target and the guided spacecraft by controlling the propulsive force of the auxiliary propulsion device according to the relative speed. and control the timing of the guided projectile's proximity fuse to optimize it.

[0017] In addition to the effects of the fifth invention, the sixth invention of the present invention determines whether the guided projectile will directly hit the target based on the error signal, and if it is determined that the guided projectile will hit the target directly,
The guided projectile is controlled to slow down the guided projectile, increase its relative speed as much as possible, and increase the damage it inflicts on the target when it meets the target.

[0018]

[Example] Example 1. FIG. 1 is a diagram showing Embodiment 1 of the present invention, in which 1 to 15 and 19 to 24 are the same as the conventional device shown in FIG. 11, and 26, 29, and 30 to 33 are new to the conventional device. This is a device added to the However, conventionally they were attached almost sequentially from the tip in the propulsion direction.
The components from antenna 6 to propulsion device 24 are attached to propulsion device 2.
Except for No. 4, the arrangement is reversed, and instead of flying in the direction of the meeting point with Target 1, it is now set to fly in the same direction as Target 1's flight direction on the predicted flight trajectory of Target 1. It is a device controlled by 26 calculates the relative distance to the target 1 from the output of the error signal generator 9, determines whether it is within a predetermined relative distance, and outputs a low level signal when the distance is beyond the predetermined relative distance. These days, 29 is an operation period determination circuit that outputs a high-level signal, 29 is an auxiliary propulsion device that accelerates the guided missile M when the output of the operation period determination circuit becomes a high-level signal, and 30 is an auxiliary propulsion device that accelerates the guided vehicle M. After that, a propulsion device disconnection mechanism separates the auxiliary propulsion device and the propulsion device; 31 is a propulsion device disconnection detection circuit that detects that the propulsion device has been disconnected and outputs a disconnection signal; 32 is a disconnection signal input from the disconnection detection circuit 31; An aircraft settling delay circuit 33 outputs a start command signal after a period of time has elapsed from when the aircraft settles to when the aircraft settles;
This is an operation start command circuit that outputs an operation command signal for starting the operation of the receiver, antenna, etc.

In the guided flying vehicle M configured as described above, as shown in FIG. When the relative distance is controlled to fly in the same direction as the flight direction and the relative distance is within a predetermined distance, it is accelerated by the auxiliary propulsion device 29 as shown in Fig. 3, and when the relative distance after acceleration is within the predetermined distance, as shown in Fig. 4 Street propulsion device 24
The antenna 6 attached to the front of the propulsion device 24 is directed toward the target 1, and after locking on to the target 1, the antenna 6 is directed toward the meeting point A with the target 1 (target 1) as shown in FIG.
When target 1 autonomously guides itself to the predicted flight trajectory Tt) and finally passes near the guided projectile M (there is no problem if it hits directly), the timing of detonation can be adjusted because the relative speed can be made smaller than before. It is now possible to take guided projectiles M
This will prevent the incapacitation of Note that the timing of acceleration by the auxiliary propulsion device and the timing of disconnection of the propulsion device separation mechanism can be expected to be optimized by operating at a relative distance that satisfies the following equations (1) and (2).

[0020]

[Math 1]

[0021]

[Math 2]

Example 2. FIG. 6 is a diagram showing Embodiment 2 of the present invention.
33 are the same as those in FIG. 1, and 34 is a device newly added to FIG. 34 is a separation target direction control device that separates the separation direction of the propulsion device 24 and the auxiliary propulsion device 29 in the direction of the target 1 based on the error signal output from the error signal generator 9, so as to cause even the slightest damage to the target 1. .

In the guided spacecraft M configured as described above, the guided spacecraft M moves toward the target 1 by the propulsion device 2.
4 and the auxiliary propulsion device 29, there is a possibility that the target 1 will collide with the propulsion device 24 or the auxiliary propulsion device 29 and receive damage, thereby improving the ability to shoot down the target 1.

Example 3. FIG. 7 is a diagram showing Embodiment 3 of the present invention, 1 to 15, 19 to 24, 26, 29,
33 are the same as those in FIG. 1, and 35 is a device newly added to FIG. Reference numeral 35 indicates that the propulsion device 24 and the auxiliary propulsion device 29 are separated in a direction other than the direction of the target 1 based on the error signal output from the error signal generator 9, and when the target 1 is captured, the separated propulsion device 24 and the auxiliary propulsion device 29 are separated from each other. This is a separation target direction out-of-direction control device for locking on to the target 1 as quickly as possible without the device 29 getting in the way.

In the guided spacecraft M configured as described above, the guided spacecraft M separates the propulsion device 24 and the auxiliary propulsion device 29 in a direction other than the target direction. When the guided flying object M locks on to the target 1, the device 29 can lock on to the target 1 quickly because it is out of the field of view in the direction of the target 1, improving the accuracy of guiding to the target 1 and improving the performance of shooting down the target.

Example 4. FIG. 8 is a diagram showing Embodiment 4 of the present invention.
33 are the same as those in FIG. 1, and 36 and 37 are devices newly added to FIG. 36 is an error signal generator 9
A relative speed determination circuit 37 outputs a high level signal if the relative speed is faster than a predetermined speed, and outputs a low level signal if it is slower than a predetermined speed. The separation direction of the propulsion device 24 and the auxiliary propulsion device 29 is set as the target direction, and when a low level signal is input, the separation direction of the propulsion device 24 and the auxiliary propulsion device 29 is set as the target direction.

In the guided spacecraft M configured as described above, when the relative speed between the guided spacecraft M and the target 1 is high, the propulsion device 24 and the auxiliary propulsion device 29 are separated in the direction of the target 1. , there is a possibility that the target 1 will collide with the propulsion device 24 or the auxiliary propulsion device 29 and receive damage. (Due to the high relative speed, it is difficult to avoid target 1 even if the target 1 makes a sharp turn.) Also, when the relative speed between the guided flying object M and target 1 is low, the propulsion device 24 and the auxiliary propulsion device 29 are By separating away from the target direction, it will not become an obstacle when locking on, and it will be able to lock on to target 1 quickly, so even if target 1 makes a sharp turn, it will be able to follow target 1 without losing sight of it. Improves the ability of guided flying object M to shoot down target 1.

Example 5. FIG. 9 is a diagram showing Embodiment 5 of the present invention.
33, 36, and 37 are the same as those in FIG. 8, and 38 is a newly added device to FIG. 38 is an auxiliary propulsion device control device that controls the propulsive force of the auxiliary propulsion device 29 according to the relative speed output from the relative speed determination circuit 36.

In the guided spacecraft M configured as described above, the propulsive force of the auxiliary propulsion device is controlled according to the relative speed, so the approach speed at the time of meeting with the target 1 is determined as the optimum timing for the proximity fuze. It becomes possible to set the target range, and it is possible to improve the ability of the guided flying object M to shoot down targets.

Example 6. FIG. 10 is a diagram showing Embodiment 6 of the present invention.
0 to 33, 36 to 38 are the same as in Figure 9, and 39, 40
is a new device added to FIG. 39 is a direct hit determination circuit that determines whether or not there will be a direct hit on the target 1 based on the error signal output from the error signal generator 9; This is a deceleration device that decelerates the flying object M and increases its relative speed with the target 1.

In the guided projectile M configured as described above, in the case of a direct hit, the projectile M is decelerated and directed toward the target 1.
Increase the relative speed with target 1 to increase the impact effect with target 1 during the meeting, and if there is no direct hit, decelerate the projectile M and target 1.
By slowing down the relative speed with respect to the guided flying object M, the timing of the proximity fuse of the guided flying object M can be improved, so that the ability of the guided flying object M to shoot down a target can be improved.

[0032]

Effects of the Invention With the configuration as described above, the present invention has the effect of preventing the guided flying vehicle M from becoming incapacitated against a small ultra-high-speed target and improving the ability to shoot down the target.

Furthermore, since there is no antenna attached to the front part in the propulsion direction, only the aerodynamic characteristics need be considered for the shape of the tip without considering the electrical characteristics, so it is possible to increase the speed and extend the flight distance.

[Brief explanation of the drawing]

FIG. 1 is a configuration block diagram showing a first embodiment of the present invention.

FIG. 2 is an explanatory diagram showing the relative positional relationship between the guided flying object of the present invention and a target immediately after it is launched from a launcher.

FIG. 3 is an explanatory diagram showing the relative positional relationship between the guided flying object of the present invention and the target when the guided flying object reaches the timing distance for acceleration.

FIG. 4 is an explanatory diagram showing the relative positional relationship between the guided flying object of the present invention and the target when the timing distance for separating the propulsion device, etc. is reached.

FIG. 5 is an explanatory diagram showing the relative positional relationship between the guided flying object of the present invention and the target until it meets the target after separating the propulsion device and the like.

FIG. 6 is a configuration block diagram showing a second embodiment of the present invention.

FIG. 7 is a configuration block diagram showing a third embodiment of the present invention.

FIG. 8 is a configuration block diagram showing a fourth embodiment of the present invention.

FIG. 9 is a configuration block diagram showing a fifth embodiment of the present invention.

FIG. 10 is a configuration block diagram showing a sixth embodiment of the present invention.

FIG. 11 is a configuration block diagram showing a conventional device.

[Explanation of symbols]

1 Target 2 Transmitted wave 3 Reflected wave 4 Transmitter 5 Circulator 6 Antenna 7 Receiving device 8 Inertial navigation device 9 Error signal generator 10 Antenna servo device 11 Steering device 12 Emitter 13 Command signal 14 Command receiving antenna 15 Command receiver 19 Proximity Fuze 20 Arrival tube 21 Detonation signal generation circuit 22 Ammunition 23 Power supply 24 Propulsion device 26 Operation period determination circuit 29 Auxiliary propulsion device 30 Propulsion device separation mechanism 31 Propulsion device separation detection circuit 32 Aircraft settling delay circuit 33 Operation start command circuit 34 Separation target Direction control device 35 Separation target direction outside control device 36 Relative speed determination circuit 37 Separation direction control device 38 Auxiliary propulsion device control device 39 Direct hit determination circuit 40 Deceleration device A Meeting point g with target Acceleration M Guided projectile T1 Auxiliary propulsion Device acceleration time T2 Detachment time T2 ' Required lock-on time T3 Required guidance flight time T4
Settling time TM Flight trajectory of guided projectile Tt
Predicted flight trajectory of the target Vc Relative velocity at the start of acceleration

Claims (6)

[Claims] Claim 1: A transmitter that generates a transmission signal of a transmission wave to irradiate a target, and a transmitter that supplies the transmission signal to an antenna but not to a receiving device, and supplies the signal received by the antenna to the receiving device. A circulator that does not supply the signal to the transmitter, an antenna that irradiates the transmitted signal to the target and receives reflected waves from the target, and a target lock-on signal and a target signal after target lock-on from the signal received by the antenna. an inertial navigation position that generates position and velocity information after launch from the launcher; an error signal generator that extracts an error signal from the target signal or target command signal and position/velocity information; an antenna servo device that drives the antenna in the target direction based on the error signal; a steering device that steers the antenna in the direction of the meeting point with the flight path based on the error signal; a command antenna that receives the command signal from the launcher; and the command antenna that receives the command signal from the launcher. A command receiver extracts the target command signal from the command signal received by the antenna, a proximity fuze generates a proximity detonation pulse at a timing according to the relative speed when passing near the target, and a proximity fuse generates the landing detonation pulse when it hits the target directly. A detonation signal generation circuit that generates a detonation signal to detonate the ammunition by the proximity detonation pulse or the arrival detonation pulse, and when they meet with the target, the detonation signal causes an explosion, causing great damage to the target. In a guided flying vehicle that is equipped with ammunition, a power supply that supplies the necessary power to the components, and a propulsion device that provides power, the following antennas are attached in approximately order from the tip in the propulsion direction.
The components up to the propulsion device are arranged in reverse order except for the propulsion device, and the relative distance to the target is calculated and it is determined whether or not it is within a predetermined relative distance. and an operation period determination circuit that outputs a high-level signal when near a predetermined relative distance, and when the output of the operation period determination circuit becomes a high-level signal, activates the auxiliary propulsion device and accelerates the guided flying object. After that, the auxiliary propulsion system, the propulsion system disconnection mechanism that disconnects the propulsion system, the propulsion system disconnection detection circuit that detects that the propulsion system has been disconnected and outputs a disconnection signal, and the aircraft stabilizes after the disconnection signal is input. The aircraft settling delay circuit outputs the start command signal after the time has elapsed, and the start command signal
A dielectric flying object characterized by comprising an operation start command circuit that outputs an operation command signal for starting the operation of a transmitter, a receiver, an antenna, and an antenna servo. 2. The guided spacecraft according to claim 1, further comprising a separation target direction control device for separating the separation direction of the propulsion device toward the target direction based on the error signal and causing even the slightest damage to the target. A derivative projectile characterized by 3. The guided spacecraft according to claim 1, further comprising a separation target direction control device for separating the propulsion device in a direction other than the target direction based on the error signal and locking onto the target as quickly as possible. A guided flying object characterized by comprising: 4. The guided flying object according to claim 1, wherein a relative speed determination circuit outputs a high level signal when the relative speed is faster than a predetermined speed according to the speed information, and outputs a low level signal when it is slower. , characterized by comprising a disconnection direction control device that sets the disconnection direction of the propulsion device to the target direction when a high level signal is input, and sets the disconnection direction of the propulsion device to a direction other than the target direction when a low level signal is input. Derivative projectile. 5. The guided spacecraft according to claim 4, further comprising an auxiliary propulsion device control device that controls the propulsive force of the auxiliary propulsion device in accordance with relative speed. 6. The guided missile according to claim 5, further comprising: a direct hit determination circuit that determines whether or not it will directly hit the target based on the error signal; A guided flying object characterized by being equipped with a deceleration device that increases relative speed.