JP3301871B2 - Guided flying object - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an improved guided flying object that flies toward a target object and destroys the target object.

[0002]

2. Description of the Related Art First, a conventional guided flying object will be described with reference to FIG. In the figure, 1 is a guided flying object,
2 is a target object, 3 is a radar transmission wave, 4 is a radar reception wave,
Reference numeral 5 denotes a proximity fuze transmission wave, and reference numeral 6 denotes a proximity fuze reception wave.

In the above configuration, the guided flying object 1 transmits the radar transmission wave 3 toward the target object 2 and
A radar transmission wave 3 reflected by the antenna is received as a radar reception wave 4. The guidance vehicle 1 approaches the target object 2 by operating the wing while always receiving the radar reception wave 4.

[0004] At the same time, the guided flying vehicle 1 has a radar transmission wave 3
And a weak radio wave having a different frequency is transmitted as the proximity fuze transmission wave 5, and when the guided flying object 1 approaches the target object 2, the reflected wave is received as the proximity fuze reception wave 6.
The guidance vehicle 1 explodes the warhead incorporated in the guidance vehicle 1 using the proximity fuze reception wave 6 as a trigger to destroy the target object 2. The above is the operation of the guided flying object.

Next, a specific configuration and operation of the conventional guided flying object will be described. FIG. 14 is a configuration diagram of a conventional guided flying object, 7 is a radar antenna, 8 is a directional coupler, 9 is a radar receiver, 10 is an angle error detection circuit,
11 is an antenna driving device, 12 is a radar transmitter, 13 is an auto pilot, 14 is a steering device, 15 is a wing, 16 is a frequency mixer, 17 is a detector, 18 is a proximity fuze, 19 is a proximity fuze transmitting antenna, and 20 is A transmitter, 21 is a proximity fuze receiving antenna, 22 is a receiver, 23 is a target proximity detection circuit, 24 is a detonator, 25 is a warhead, and 26 is an inertial reference device.

Next, the operation will be described with reference to FIGS. The high-frequency power output from the radar transmitter 12 in FIG. 14 is supplied to the radar antenna 7 through the directional coupler 8, and becomes the radar transmission wave 3 in FIG.
It is radiated toward. This radar transmission wave 3 is the target object 2
Is reflected by the antenna and becomes a radar reception wave 4, which is received by the radar antenna 7. The radar antenna 7 has the radar reception wave 4
Is converted to an electric signal and sent to a radar receiver 9 via a directional coupler 8. The radar receiver 9 amplifies the electric signal and outputs the electric signal to the angle error detection circuit 10 and the frequency mixer 16.
The angle error detection circuit 10 receives the electric signal, detects an angle error of the radar antenna with respect to the target, and outputs a control signal to the antenna driving device 11 so that the strength of the signal received by the radar receiver 9 is maximized. The radar antenna 7 is angle-tracked in the direction of the target object 2.

Further, the control signal of the angle error detection circuit 10 is also sent to the auto pilot 13. On the other hand, the inertial reference device 26 measures the angular velocity and acceleration as the inertial information of the guided flying object, and the autopilot 13 causes the guided flying object to fly toward the target object 2 based on the control signal and the inertial signal. The steering command is sent to the steering device 1
Send to 4. The steering device 14 controls the wing 15 based on a steering command. In this way, the radar antenna 7 of the guided flying object is always controlled in the direction of the target object 2, and the guided flying object flies in the direction of the target object 2 under the control of the wings 15.

The received signal of the radar receiver 9 sent to the frequency mixer 16 is compared in frequency with the radar transmission frequency of the radar transmitter 12 by the frequency mixer 16, and the difference between the two is sent to the detector 17 as a Doppler frequency. . The detector 17 converts the Doppler frequency into a DC voltage, detects a sudden frequency change, and sends a closest approach signal to the detonator 24. The Doppler frequency represents the approach speed between the guided flying object and the target object 2, and has a characteristic that it suddenly changes to 0 at the moment when the guided flying object approaches and approaches the target object 2.

On the other hand, the transmitter 20 of the proximity fuze 18 radiates a weak radio wave having a frequency different from that of the radar transmission wave 3 from the proximity fuze transmission antenna 19 as the proximity fuze transmission wave 5. Since the proximity fuze transmission wave 5 is weak, the proximity fuze reception wave 6 is reflected from the target object 2 and received by the proximity fuze reception antenna 21 only when the guided flying object approaches the target object 2. The receiver 22 amplifies the radio wave received by the proximity fuze receiving antenna 21 and sends it to the target proximity detection circuit 23 as a proximity signal. The target proximity detection circuit 23 sends a detection signal indicating that the target object 2 has been detected to the detonator 24 when the intensity of the proximity signal from the receiver 23 becomes equal to or greater than a predetermined value. When both the closest signal from the detector 17 and the detection signal from the target proximity detection circuit 23 are obtained, the detonating device 24 emits a detonating signal for detonating the warhead 25 and detonates the warhead 25. The warhead 25 emits a large number of projectiles to the periphery by explosion. This bullet hits the target object 2 and destroys the target object 2.

[0010]

The conventional guided flying vehicle is constructed as described above, and the timing of detonating the warhead is determined mainly by a sudden change of the Doppler frequency obtained from the radar transmission wave and the radar reception wave. Therefore, when the shape of the target object is complicated, the intensity of the radar reception wave becomes unstable and the sudden change of the Doppler frequency cannot be accurately captured,
Since the detonation timing of the warhead is unstable and the detonation timing of the warhead is determined by the sudden change of the Doppler frequency, that is, the closest approach between the target object and the guided flying object, the approach speed relative angle between the target object and the guided flying object There was a problem that the target object could not be correctly destroyed due to the inability to cope with the change of the target object.

SUMMARY OF THE INVENTION It is an object of the present invention to solve the above-described problems and to provide a guided flying object capable of setting a detonation delay time at which a warhead can accurately destroy a target object.

[0012]

SUMMARY OF THE INVENTION A guided flying object according to the present invention is provided with a detonation delay calculation device for a warhead, and obtains from a radar transmitter and a radar receiver a detection signal of a target object by a proximity fuse as a reference time. a Doppler frequency that is, the direction of the radar antenna, induced a bullet piece rate warhead flying object is the eigenvalue, the timing of initiation of the warhead with a radio wave transmission direction of proximity fuse, the mounting position of the warhead and proximity fuse Is calculated.

Further, the guided flying object according to the present invention can fly the target object based on the approach speed of the target object and the guided flying object, the swing angle of the radar antenna, and the flying speed of the guided flying object from the inertial reference device. A target speed estimating circuit for estimating the speed, an aspect angle between the target and the guided flying object based on the approach speed of the target and the guided flying object, the swing angle of the radar antenna, and the flying speed of the guided flying object from the inertial reference device The target aspect angle estimating circuit for estimating the warhead is calculated using the target speed and the aspect angle.

In the guided flying object according to the present invention, a target shape storage circuit for storing shape information of a target object which may be an attack target of the guided flying object and a type of the target object to be attacked are set. A target type setting circuit is used to calculate the timing of detonating the warhead by using information of the set target object.

The induction flying body according to the invention has a target type selection circuits for selecting the target of attack to be addressed using the altitude information of the inertial reference unit, also using the information of the set target The timing at which the warhead detonates is calculated.

Further, the guided flying object according to the present invention comprises:
A target type selection circuit for selecting the target object of the attack target from the received signal strength of the radar receiver and the relative distance between the guided flying object and the target object obtained from the radar receiver, and the set target The timing of detonating the warhead is calculated using the shape information of the object.

[0017]

Since the detonation delay time calculation device for a guided flying object according to the present invention calculates the detonation timing and detonates the warhead, the detonation timing of the warhead can be appropriately controlled in accordance with the approach speed and the relative angle with the target object.

Further, since the detonation delay time calculation apparatus for a guided flying object according to the present invention calculates the detonation timing and detonates the warhead, it is possible to appropriately control the detonation timing of the warhead according to the aspect angle with the target object. .

Since the detonation delay time calculation apparatus for a guided flying object according to the present invention can also set the shape information of the target object, the detonation timing of the warhead can be further appropriately controlled in accordance with the target object.

Further, the detonation delay time calculation apparatus for a guided flying object according to the present invention can use information on the altitude at which the target object flies, so that the detonation timing of the warhead can be further adjusted according to the most conceivable target object at the obtained altitude. Can be appropriately controlled.

The detonation delay time setting device for a guided flying object according to the present invention can also use the information on the intensity and distance of the reflected radio wave of the target object, so that the detonation timing of the warhead can be appropriately controlled according to the target object.

[0022]

【Example】

Embodiment 1 FIG. Hereinafter, an embodiment of the present invention will be described. FIG. 1 is a configuration diagram of a guided flying object according to a first embodiment of the present invention. In FIG.
Is a directional coupler, 9 is a radar receiver, 10 is an angle error detection circuit, 11 is an antenna driving device, 12 is a radar transmitter, 13 is an auto pilot, 14 is a steering device, 15 is a wing, 16 is a frequency mixer, 17 is a detector, 18 is a proximity fuze, 19 is a proximity fuze transmitting antenna, 20 is a transmitter, 21
Is a proximity fuze receiving antenna, 22 is a receiver, 23 is a target proximity detection circuit, 24 is an explosion device, 25 is a warhead, 26 is an inertial reference device, 27 is an explosion delay time calculation device, 28 is an approach speed calculation circuit, and 29 is an approach speed calculation circuit. An approach speed storage circuit, 30 is a swing angle storage circuit, 31 is a unique parameter storage circuit, 32 is a detonation delay time calculation circuit, and 33 is a detonation signal generation circuit.

Next, the operation of the above embodiment will be described with reference to FIGS .
This will be described with reference to FIG. The high-frequency power output from the radar transmitter 12 shown in FIG. 1 is supplied to the radar antenna 7 through the directional coupler 8, and is radiated toward the target object 2 as the radar transmission wave 3 shown in FIG. This radar transmission wave 3
Is reflected by the target object 2 and becomes a radar reception wave 4,
The signal is received by the radar antenna 7. The radar antenna 7 converts the radar reception wave 4 into an electric signal, and sends the electric signal to the radar receiver 9 via the directional coupler 8. The radar receiver 9 amplifies the electric signal, and outputs an angle error detection circuit 10 and a frequency mixer 16
Output to The angle error detection circuit 10 outputs a control signal to the antenna driving device 11 so that the strength of the reception signal of the radar receiver 9 becomes maximum, and the radar antenna 7 outputs the control signal to the target object 2.
Angle tracking in the direction of.

Further, the control signal of the angle error detection circuit 10 is also sent to the auto pilot 13. On the other hand, the inertial reference device 26 measures the angular velocity and acceleration as the inertial information of the guided flying object, and the autopilot 13 causes the guided flying object to meet the target object 2 based on the control signal and the inertial signal. A steering command is sent to the steering device 14 so as to fly toward. The steering device 14 controls the wing 15 based on a steering command. In this way, the radar antenna 7 of the guided flying object is always controlled in the direction of the target object 2, and the guided flying object flies in the direction of association with the target object 2 under the control of the wing 15.

On the other hand, the received signal f _R of the radar receiver 9 sent to the frequency mixer 16 is compared in frequency with the radar transmission frequency f _O of the radar transmitter 12 by the frequency mixer 16, and the frequency difference between the two is taken as the Doppler frequency f _d. It is sent to the approach speed calculation circuit 28 of the detonation delay time calculation device 27. The radar transmission frequency f _O of the radar transmitter 12 is also sent to the approach speed calculation circuit 28 together with the Doppler frequency f _d , and the approach speed V _c between the guided flying object 1 and the target object 2 is calculated by equation (1), and the approach speed is calculated. It is sent to the storage circuit 29. Here, in equation (1), c means the speed of light, and indicates the relationship between the Doppler frequency and f _d , the radar transmission frequency f _O and the approach speed V _c .

[0026]

(Equation 1)

At the same time, an antenna angle signal λ corresponding to the direction of the radar antenna 7 is sent from the antenna driving device 11 to the swing angle storage circuit 30 of the detonation delay time calculation device 27.

The signals sent to the approach speed storage circuit 29 and the swing angle storage circuit 30 output stable information that avoids sharp fluctuations when passing near the target object by outputting information delayed by a predetermined time. I do.

On the other hand, the transmitter 20 of the proximity fuze 18 radiates a weak radio wave having a frequency different from that of the radar transmission wave 3 from the proximity fuze transmission antenna 19 as the proximity fuze transmission wave 5. Since the proximity fuze transmission wave 5 is weak, the proximity fuze reception wave 6 is generated only when the guided flying object approaches the target object 2.
And is received by the proximity fuze receiving antenna 21. The receiver 22 amplifies the radio wave received by the proximity fuze receiving antenna 21 and sends it to the target proximity detection circuit 23 as a proximity signal. Target proximity detection circuit 23 initiation signal generating circuit of the detonator delay time detection signal indicating the detection of the target object 2 when the intensity of the proximity signal exceeds a specific value determined in advance from the receiver 22 the computing device 27 Send to 33.

[0030] and the approach speed V _c obtained from the approach speed memory circuit 29 as a reference time a detection signal from the detonator delay time calculation unit 27 target proximity detection circuit 23, an antenna angle signal from the swing angle storage circuit 30, The trajectory velocity V _e of the warhead, which is the eigenvalue of the guided flying vehicle stored in the eigenparameter storage circuit 31, the transmission direction α of the proximity fuze transmission wave,
Using the distance E between the proximity fuze 18 and the mounting position of the warhead 25, the timing of firing the warhead is determined by the firing delay time calculation circuit 3.
2 to generate an explosion signal for exploding the warhead 25 with a delay by the time obtained by the operation, thereby exploding the warhead 25. The warhead 25 scatters a large number of bullets around due to explosion. This bullet destroys the target object 2.

The explosion delay time calculation device 2 is shown in FIGS.
7 will be described in detail. Figure 2 shows the guided flying object 1
FIG. 7 is a diagram showing a state before a target object 2 has passed through the vicinity. Here flight is carried out by a proportional navigation, flight is continued such that the velocity vector V _T of the velocity vector V _m and the target object induction flying object as shown in Figure 2 constituting the associated triangle. This process is continued until the vehicle passes the vicinity of the target. In this case, the swing angle λ, the line of sight between the guidance flying object 1 and the target object 2 and the aspect angle Θ formed by the target object, the approach speed V _c , the guidance between the velocity vector V _T of the velocity vector V _m and the target object flying object, relationship indicated by equation (2), equation (3). Equation (2) is an expression showing the approach speed V _c, the formula (3) is a relational expression constituting the associated triangular line connecting the target and the flying object is moved in parallel.

[0032]

(Equation 2)

Next, a state when the guided flying object 1 and the target object 2 meet will be considered. FIG. 3 shows that the guidance spacecraft 1 and the target object 2 meet, and the proximity fuse 18 of the guidance spacecraft 1
FIG. 4 is an explanatory diagram showing a state in which the target object 2 is detected, a warhead 25 is detonated, and a bullet of the warhead 25 hits the target object 2. In the figure, V _e is the trajectory velocity of the warhead, α is the transmission direction of the proximity fuze transmission wave, E is the distance between the mounting position of the proximity fuze 18 and the warhead 25, Z ₀ is the target detection distance of the proximity fuze, and Z ₁ is the distance to the warhead. The distance when the target object passes laterally is shown. At time t = 0, the proximity fuze 18 detects the target object 2, and at time t = td, the warhead 2
5 and the conditions under which the rams hit the target object 2 can be approximated by the relationship shown in equation (4).

[0034]

(Equation 3)

[0035] In this state, approach speed V _c shown in FIG. 2 is the same as the relative velocity vector V _R, the angle of the relative velocity vector V _R to the induction spacecraft radar of Figure 2
This can be regarded as substantially equal to the antenna swing angle λ .
Therefore, in order to apply the approach speed and the swing angle as stable information at the time of passing near the guidance vehicle, the approach speed storage circuit 29 and the swing angle storage circuit 30 store stable information before the transition period. Delay time calculation circuit 32
Used in. Here, the target detection distance of the proximity fuze uses a required set value, and the distance when the warhead passes laterally needs to be set from the guidance accuracy of the guided flying object. The above is the operation of the detonation delay time calculation device 27 .

In the above-described embodiment, an example is shown in which the radar vehicle is provided with a radar transmitter and a radar receiver. However, it is only necessary to obtain radar transmission waves and radar reception waves in order to know the approach speed. , induced spacecraft aircraft or firing, also compromising the effect of the present invention in the induction flying object that does not have a record over da transmitter when radar waves from a ground radar system to the target object is irradiated There is no. Further, although an example in which radio waves are used for the proximity fuze has been described, it is only necessary that the target object can be detected at a short distance, and a proximity fuze using light may be used.

Embodiment 2 FIG. In the first embodiment, the target object is considered as a mass point, but a method of calculating the delay time on the assumption that the object has a width and a length can set the delay time more appropriately. 4 and 5 show the relationship. In FIG. 4, 7 to 33 are the same as those in the first embodiment, 34 is a target speed estimating circuit, 35
Indicates a target aspect angle estimation circuit. Expressions (5) and (6) shown below are calculated from Expressions (2) and (3). Equation (5) is the flying speed V _{m of} the guided flying vehicle, the swing angle λ of the guided flying vehicle, the approach speed V _c , and the target speed V _T.
Is a formula for estimating the target aspect angle θ from the following equation.
Is the flying speed of the guided vehicle V _m , the guided vehicle
Radar antenna swing angle λ of a formula for estimating the target speed V _T from the approach speed V _c.

[0038]

(Equation 4)

FIG. 5 shows the detonation delay time in consideration of the size of the target object . In the figure, L
a and Lb model the size of the target object , and Lc indicates the length of the target object observed from the guided flying object. If it is desired to hit a bullet at the center of a large target, a delay corresponding to half the length of the target object observed from the guided vehicle is required. In this case, the relationship between the length Lc of the target object observed from the guided flying object, La and Lb obtained by modeling the size of the target object , the detonation delay time td, and the like are expressed by equations (7) and (8). ) And (9). Equation (7) is an expression for calculating the length of the target projected onto the induction flying object, the target length La is the target aspect angle θ and Re of
The target length Lb is projected to the target aspect angle θ and the radar antenna.
Projected to the cosine length of the difference in the tena swing angle λ. Equation (8) is an equation for calculating the length Ld of the target detection point of the guided flying object and the center point of the target object.
A projection distance Z _O cos [alpha] of _O to induction flying object, and the distance E of the mounting position of the proximity fuse 18 and the warhead 25, the sum of half the target length Lc. Equation (9) is an equation for calculating the delay time td, and the time (Ld / Ld / L) for the target object to pass through the length Ld of the center point between the target detection point of the guidance vehicle and the target object.
V _c cosλ) and bullet piece, which is the difference between the transit time through the distance Z _l of warhead bullet pieces velocity V _e between the warhead and the target object.

[0040]

(Equation 5)

Embodiment 3 FIG. In the second embodiment, only one type of target model is used. However, target objects are classified into large targets and small targets. 6, 7, and 8 show examples in which the type of the target object can be set. FIG. 6 shows a target type setting circuit 36 and a target type setting circuit 37.
Is a target shape memory circuit, and the other is the same as the second embodiment. FIG. 7 shows an example in which a large target is modeled, and FIG. 8 shows an example in which a small target is modeled. The modeled target object is stored in the target shape storage circuit 37, and a signal is sent to the detonation delay time calculation circuit 32 in accordance with a command from the target type setting circuit 36. The command of the target type setting circuit 36 can be set immediately before the launch of the guided vehicle, or the guided vehicle can be launched.
It is also possible to set after launch by a command from the aircraft or the ground. Equations (10) to (15) show the relational expressions for setting the delay time. Equations (10) and (11) are equations for calculating the length of the target projected on the guided flying vehicle, similar to equation (7). Equation (10) is an equation (11) for a small target. Indicates the case of a large target. Equations (12), (1
3) is a formula for calculating the length of the target detection point of the guidance vehicle and the center point of the target, as in formula (8). Is shown. Equation (14), (15) is an expression for calculating the same delay time td and the formula (9), equation (14) for small target, formula (15) shows the case of a large target.

[0042]

(Equation 6)

Embodiment 4 FIG. In the third embodiment, it is necessary to set the target object from the outside by the target type setting circuit 36. However, the target type can be set independently by considering the main operation area of the target object in advance.
Class selection is possible. Fourth Embodiment In a fourth embodiment, an example in which a target is selected using altitude information of the inertial reference device will be described. In FIG. 9, reference numeral 38 denotes a target type selection circuit for selecting a target object by altitude, and the other components are the same as those of the third embodiment. Figure 10 shows altitude and target
3 shows the relationship between object models. In the figure, the horizontal axis target object <br/> shape model, and the vertical axis shows the high degree of the target object is mainly fly. When the altitude detected by the inertial reference device 26 is input to the target type selection circuit 38, a target object corresponding to the altitude is selected. This is an example in which low altitude and high altitude are modeled as small targets and medium altitude is a large target.

Embodiment 5 FIG. In the fourth embodiment, the target object is selected according to the altitude.
It is also possible to distinguish between a small target and a large target based on the radar reflection area (RCS) of the target object captured by the guided flying object , which is an index of the size of the target object. In FIG. 11, 3
9 is a relative distance detection circuit, 40 is a target RCS estimation circuit,
Reference numeral 1 denotes a target type selection circuit, and the other components are the same as those in the fourth embodiment. FIG. 12 shows an example of a target selection criterion based on the radar reflection area. The vertical axis indicates the radar reflection area, and the horizontal axis indicates the aspect angle θ . The target radar reflection area is the aspect angle θ
And it is necessary to make a determination according to the aspect angle θ . Equation (16) shows the method of calculating the radar reflection area. Equation (16) is a logarithmic notation radar equation.
The radar reflection area is the fourth power of the distance R and the signal-to-noise ratio (S /
N) . Here, K is an eigenvalue determined by radar characteristics.

[0045]

(Equation 7)

[0046]

As described above, according to the present invention, the detonation delay time calculation device is provided for the guided flying object, and the angle, approach speed, and radar speed of the radar antenna are determined using the detection signal of the target object detected by the proximity fuse as the reference time. Since the detonation timing is calculated from the characteristic value of the guided flying vehicle to detonate the warhead, an effective target defeat can be performed.

According to the present invention, not only the angle of the radar antenna, the approach speed, and the eigenvalues of the guided flying object, but also the flying speed of the target object and the aspect angle with the guided flying object can be estimated. It can be perceived as being wide and long, and it can destroy the right place on the target that fits.

According to the present invention, a target object to be dealt with by the guided flying object can be set from the outside, so that an appropriate portion of the set target having a spread and length can be destroyed.

[0049] Further, since it is possible to set a highly target object corresponding from altitude information of induction spacecraft according to the present invention, autonomously without setting action target object from the outside, and spread You can destroy a long target at an appropriate point.

According to the present invention, the type of the target object to be dealt with can be set from the radar information of the guided flying object. Therefore, the spread and length can be autonomously set without setting the target object to be dealt with from outside. Can be destroyed at an appropriate point on a target that has a target.

[Brief description of the drawings]

FIG. 1 is a configuration diagram of a guided flying object according to Embodiment 1 of the present invention.

FIG. 2 is an explanatory diagram showing a relationship between a target object and a terminal guidance stage of a guided flying object.

FIG. 3 is an explanatory diagram for explaining an operation of the present invention, and is a diagram showing a relationship between a target object and a guided flying object at the time of a meeting;

FIG. 4 is a configuration diagram of a guided flying object according to a second embodiment of the present invention.

FIG. 5 is an explanatory diagram for explaining the operation of the present invention, and is a diagram showing a relationship between a modeled target object having a length at the time of meeting and an expanse and a guided flying object.

FIG. 6 is a configuration diagram of a guided flying object according to a third embodiment of the present invention.

FIG. 7 is an explanatory diagram illustrating modeling of a large target.

FIG. 8 is an explanatory diagram illustrating modeling of a small target.

FIG. 9 is a configuration diagram of a guided flying object according to Embodiment 4 of the present invention.

FIG. 10 is an explanatory diagram illustrating the relationship between the setting of the target size according to the altitude.

FIG. 11 is a configuration diagram of a guided flying object according to Embodiment 5 of the present invention.

FIG. 12 is an explanatory diagram showing a relationship between a target type selection device 2 that selects a target to be handled based on an aspect angle and RCS.

FIG. 13 is an explanatory diagram for explaining the operation of the guided flying object.

FIG. 14 is a configuration diagram showing a configuration of a conventional guided flying object.

[Explanation of symbols]

1 guided flying object, 2 target object, 3 radar transmission wave, 4 radar reception wave, 5 proximity fuze transmission wave, 6 proximity fuze reception wave, 7 radar antenna, 8 directional coupler,
9 radar receiver, 10 angle error detection circuit, 11 antenna driving device, 12 radar transmitter, 13 auto pilot, 14 steering device, 15 wings, 16 frequency mixer, 17 detector, 18 proximity fuze, 19 proximity fuze transmission antenna, Reference Signs List 20 transmitter, 21 proximity fuse receiving antenna, 22 receiver, 23 detection circuit, 24 detonator, 25 warhead, 26 inertia reference device, 27 detonation delay time calculation device, 28 approach speed calculation circuit, 29 approach speed storage circuit, 30 Swing angle storage circuit, 31 fixed parameter storage circuit, 32 delay time calculation circuit, 33 firing signal generation circuit, 34 target speed estimation circuit, 35 target aspect angle estimation circuit, 36 target type setting circuit, 37
Target shape storage circuit, 38 target type selection circuit, 39 relative distance detection circuit, 40 target RCS estimation circuit, 41 target type selection circuit

──────────────────────────────────────────────────続 き Continuation of front page (72) Inventor Shun Fujisawa 325 Kamimachiya, Kamakura-shi, Kamakura Works, Mitsubishi Electric Corporation (56) References JP-A-8-62329 (JP, A) JP-A-7-190692 (JP, A) JP-A-7-91900 (JP, A) JP-A-7-71897 (JP, A) JP-A-6-342066 (JP, A) JP-A-5-79293 (JP, A) JP-A-5-61691 (JP, A) JP-A-4-62398 (JP, A) JP-A-2-50100 (JP, A) (58) Fields investigated (Int. Cl. ⁷ , DB name) F42C 13 / 04 F41G 7/22-7/24

Claims (5)

(57) [Claims] 1. A radar antenna that transmits a radar transmission wave in the direction of a target object and receives a reflected wave, a radar transmitter that generates high-frequency power to the radar antenna, and a radar that amplifies a signal received from the radar antenna. A receiver, a frequency mixer that compares a frequency of a high-frequency power of the radar transmitter with a frequency of a received signal of the radar receiver and detects a frequency difference as a Doppler frequency, and a radar antenna that receives a received signal of the radar receiver and targets a target. An angle error detection circuit that detects an angle error of the antenna, an antenna driving device that causes the radar antenna to track the angle in the direction of a target object based on an output signal of the angle error detection circuit, and an acceleration and an angular velocity of the guided flying object that are measured. The inertial reference device for estimating the speed, the output signal of the angle error detection circuit and the inertial information from the inertial reference device. An autopilot that calculates a steering command from the autopilot, a steering device that controls wings based on a steering command from the autopilot, a wing that is mechanically coupled to the steering device and that is movable, and the radar transmission wave has a different frequency. A proximity fuze that transmits radio waves and receives a reflected wave when approaching the target object, and a signal indicating that the proximity of the target object has been detected when the strength of the signal received by the proximity fuze exceeds a certain value. a target proximity detection circuit that forces, in the induction flying object comprised of warhead detonate the detonation signal from the target proximity detection circuit, an antenna swing angle storage circuit for storing the antenna angle signal obtained from the antenna driving device And the approach speed to calculate the approach speed between the guided flying object and the target object from the Doppler frequency from the frequency mixer and the frequency of the radar transmission wave Calculation circuit; an approach speed storage circuit for storing the approach speed; a detection signal from the approach detection circuit; an approach speed from the approach speed storage circuit; an antenna angle signal from the antenna swing angle storage circuit; A detonation delay time calculation circuit for calculating a detonation delay time effective for destruction of a target object based on a bullet velocity of a warhead which is a characteristic value of a flying object, a radio wave transmission direction of a proximity fuse, and a mounting position of a warhead and a proximity fuse. A guided vehicle equipped with a delay time calculator. 2. The detonation delay time calculation device according to claim 1, further comprising: calculating a target speed based on an approach speed of the target object and the guided vehicle, a swing angle of the radar antenna, and a flying speed of the guided vehicle from the inertial reference device. A target speed estimating circuit for estimating the flying speed of the object, and a target based on the approach speed of the target object and the guided flying object, the swing angle of the radar antenna, and the flying speed of the guided flying object from the inertial reference device. A target aspect angle estimating circuit for estimating an aspect angle formed by the guided flying object, and inputting the target speed and the aspect angle to the detonation delay time calculation circuit, and including a target speed and an aspect angle. 2. The guidance vehicle according to claim 1, wherein the detonation delay time is estimated from the information. 3. The detonation delay time calculation device, wherein a target shape storage circuit for storing shape information of a target object that the guided flying object may be an attack target, and a target object to be attacked is designated and set. on to and a target type setting circuit, the shape information of the target object set by the target type setting circuit
Serial target shape memory via the circuit input to the detonator delay time calculation circuit, induction flying object according to claim 2 wherein the various information including the shape information of the target object and sets the initiation delay time. 4. The detonation delay time calculation device according to claim 1, wherein the target shape storage circuit stores shape information of a target which may be an attack target of the guided flying object, and the altitude information obtained from the inertial reference device. A target type selection circuit for selecting a target to be attacked and reading out the target shape information selected from the target shape storage circuit, and setting the target shape information selected by the target type selection circuit to the detonation delay. Input to the time calculation circuit, and from various information including target shape information
3. The guidance vehicle according to claim 2, wherein a detonation delay time is set. 5. A detonation delay time calculation device, comprising: a target shape storage circuit for storing shape information of a target object which may be a target of a guided flying object; a reception signal intensity of the radar receiver; A target type selection circuit for selecting the target of the attack target from the relative distance between the guided flying object and the target object obtained from the radar receiver, and reading out the target shape information selected from the target shape storage circuit. Have
Top target shape information selected by the target type selection circuit
3. The guidance vehicle according to claim 2, wherein the detonation delay time is set based on various information including target shape information input to the detonation delay time calculation circuit.