JPH10206526A - Radio jammer - Google Patents

Abstract

(57) [Summary] (Modifications) [Problem] A radio wave reflecting object emitted and dropped from an aircraft in a radio wave jamming device which emits and drops deceptive radio waves to an Doppler tracking radar and transfers tracking to the Doppler tracking radar. In addition, an effect equivalent to that of an aircraft is provided by providing an active function of correcting a change in Doppler frequency due to deceleration. An aircraft-mounted electronic device calculates a Doppler frequency predicted after the release of the release electronic device in combination with the elapsed time, sends the Doppler frequency to the release electronic device together with the emission signal, and receives the emission signal. After the activation drop electronic device 10 receives the firing signal from the airborne electronic device 1, the combination of the correction value stored in advance and its elapsed time and the combination of the Doppler frequency given from the airborne electronic device 1 and its elapsed time The frequency of the radar transmission wave received by the dropping electronic device is corrected by a correction value that satisfies a predetermined condition that enables the transition of the tracking from the Doppler frequency of the aircraft viewed from the radar.

Description

DETAILED DESCRIPTION OF THE INVENTION

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a radio wave jamming device, and more particularly to a radio wave jamming device which is an electronic device launched and dropped from an aircraft to deceive a radar reflected wave from the aircraft.

In recent years, radar has been able to track a high-speed moving object such as an aircraft by utilizing the Doppler shift of a radio wave reflected from a high-speed object in order to remove a reflected wave from the ground. I have.

On the other hand, it is necessary for aircraft to have countermeasures that can effectively deceive or obstruct such high-performance tracking radars in order to increase their survival. I have.

[0003]

2. Description of the Related Art FIG. 11 shows a technique generally known as a means by which an aircraft can deceive or obstruct radar tracking.
Is flying, the radar transmission wave 23 emitted from the Doppler radar 22 is reflected by the aircraft 21 and received by the radar 22 as a radar reflected wave 24.

At this time, when a radio wave reflecting object 50 such as aluminum foil for deceiving a Doppler tracking radar is launched and dropped from the aircraft 21, the radar reflecting area of the radio wave reflecting object 50 emitted into the air becomes larger than the reflecting area of the aircraft. Utilizing this, the reflected wave 25 from the radio wave reflecting object 50 is
2 is to be tracked, and is transferred (26) from the aircraft 21 to the radio wave reflecting object 50.

[0005] The emitted radar transmission wave 23 is reflected by the radio wave reflecting object 50 and received by the radar 22 as the radar reflection wave 25, so that the tracking of the aircraft 21 is deceived.

[0006]

In general, when a bomb or the like is dropped from an aircraft being tracked, the Doppler radar uses horizontal drag due to air resistance so as not to accidentally track the bomb or the like. It is designed not to track an object whose velocity decreases rapidly (Doppler frequency decreases).

[0007] On the other hand, a launching / dropping type radio wave reflecting object that deceives a Doppler tracking radar also has a problem that the radio wave reflecting object itself is rapidly decelerated by air resistance after launching and dropping, and the Doppler frequency is lowered.

That is, in the example shown in FIG. 12, a radio wave reflecting object 50 such as an aluminum foil is easily affected by air resistance.
Since the Doppler frequency is eliminated immediately after being fired from No. 1 and the Doppler frequency disappears (relatively the same speed as the ground), the effectiveness of tracking avoidance for the Doppler tracking type radar 22 is low.

These facts imply that it is difficult for the radio wave reflecting object emitted and dropped from the aircraft to transfer the radar tracking with a passive object that simply reflects the radar transmission wave.

Therefore, the present invention is directed to a radio wave jamming device which emits and drops deceptive radio waves to an Doppler tracking radar and transfers the tracking to a Doppler tracking object itself which is launched and dropped from an aircraft by deceleration. An object of the present invention is to provide an effect equivalent to an aircraft by providing an active function of correcting a frequency shift.

[0011]

FIG. 1 shows an example of the configuration of a radio wave jamming device according to the present invention [1]. This radio wave jamming device EA is launched and dropped from an airborne electronic device 1 and the aircraft. And a drop electronic device 10.

The airborne electronic device 1 includes a first receiving antenna 2 for receiving a radar transmission wave, and an antenna 2
A received wave analyzer 3 for analyzing the direction of arrival and frequency of the radar transmission wave received by the radar, an aircraft sensor 4 for detecting the speed and altitude of the aircraft, and the emission of the drop electronic device 10 corresponding to the speed and altitude A first storage unit 5 in which a plurality of combinations of the elapsed time after the drop and the flight speed at that time are stored in advance.
A Doppler frequency calculation unit 6 that calculates a Doppler frequency predicted after the launch and release of the dropping electronic device 10 from the combination of the elapsed time and the flight speed and the arrival direction and frequency of the radar transmission wave in combination with the elapsed time. And a launch control unit 7 for sending a combination of the Doppler frequency and the elapsed time together with a launch signal to the dropping electronic device 10.

The dropped electronic device 10 is activated upon receiving the emission signal, and is used to correct a second receiving antenna 11 for receiving a radar transmission wave and a Doppler frequency of the dropped electronic device 10. A second storage unit 12 in which a plurality of correction values are stored in advance in combination with an elapsed time after firing and dropping,
After receiving the firing signal from the airborne electronic device 1, the combination of the correction value and the elapsed time is stored in the second storage unit 12.
From the Doppler frequency given by the aircraft-mounted electronic device 1 and the correction value satisfying a predetermined condition that enables a transition of tracking from the Doppler frequency of the aircraft viewed from the radar in relation to the combination of the elapsed time. And a second Doppler frequency correction control unit 13 that outputs the second value based on the correction value output from the Doppler frequency correction control unit 13.
A modulator 14 for correcting the frequency of the radar transmission wave received by the antenna 11; an amplifier 15 for amplifying an output signal of the modulator 14; and a transmission antenna 16 for transmitting an output signal from the amplifier 15; , It consists of.

The operation of the configuration shown in FIG. 1 will be described. First, in the electronic device 1 mounted on the aircraft, the reception wave analyzer 3 determines the arrival direction and frequency of the radar transmission radio wave from the reception wave at the reception antenna 2 by using the conventional technique. To detect. When the aircraft sensor unit 4 detects the aircraft speed and altitude and gives them to the first storage unit 5, the first storage unit 5 stores the aircraft speed and altitude from the time of launch and release of the release electronic device 10 corresponding to the aircraft speed and altitude. And the combination of the elapsed time and the flight speed at that time.

The combination of the elapsed time and the flight speed is given to the Doppler frequency calculation unit 6 and used together with the arrival direction and frequency of the radar transmission radio wave output from the reception wave analysis unit 3 to be used after the launch and release of the drop electronic device 10. A combination of the predicted Doppler frequency and its elapsed time is calculated.

Then, the combination of the elapsed time and the Doppler frequency is sent from the emission control section 7 to the drop-off electronic device 10 together with the emission signal.

The dropping electronic device 10 starts operating by receiving a firing signal, and the Doppler frequency correction control unit 13 inputs the combination of the elapsed time and the Doppler frequency from the airborne electronic device 1 and stores the second storage. Part 1
2, the correction values are sequentially read out in combination with the elapsed time after the launch and release.

The Doppler frequency correction controller 13
The combination of the correction value read from the second storage unit 12 and the elapsed time indicates the relationship between the combination of the elapsed time and the Doppler frequency received from the airborne electronic device 1 based on the Doppler frequency of the aircraft viewed from the radar. It is determined whether or not a predetermined condition enabling the transfer of the tracking is satisfied, and the correction value when the predetermined condition is satisfied is output.

The correction value output from the Doppler frequency correction control unit 13 is sent to the modulation unit 14, where the frequency of the radar transmission radio wave 23 from the reception antenna 11 is Doppler-frequency corrected, amplified by the amplification unit 15, and amplified by the transmission antenna. 16 and transmitted.

As a result, the dropping electronic device 10 generates an interfering transmission wave larger than the radar reflected wave of the aircraft,
A Doppler frequency that is faster than the aircraft can be generated to shift tracking from the aircraft.

FIG. 2 shows an example of the configuration of a radio wave jamming device according to the present invention [2]. An airborne electronic device 1 comprises a first receiving antenna 2 for receiving radar transmission waves,
A received wave analyzer 3 for analyzing the direction of arrival and frequency of the radar transmission wave received by the radar, an aircraft sensor 4 for detecting the speed and altitude of the aircraft, and the emission of the drop electronic device 10 corresponding to the speed and altitude A first storage unit 5 in which a plurality of combinations of the elapsed time after the drop and the flight speed at that time are stored in advance.
A Doppler frequency calculation unit 6 that calculates a Doppler frequency predicted after the launch and release of the dropping electronic device 10 from the combination of the flight speed and the elapsed time and the arrival direction and frequency of the radar transmission wave in combination with the elapsed time. A second storage unit 81 in which a plurality of correction values for correcting the Doppler frequency of the dropping electronic device 10 are stored in advance in combination with an elapsed time after the firing and dropping; The combination of the correction value and the elapsed time is sequentially read out, and a predetermined condition for enabling the transition of the tracking from the frequency of the aircraft viewed from the radar is satisfied according to the relationship between the Doppler frequency from the Doppler frequency calculation unit 6 and the combination of the elapsed time. A determination unit 82 for reading out and outputting the data index of the combination of the correction value and the elapsed time at the time of the The index with the firing signal and the firing control unit 7 sends the-projecting under the electronic device 10, in being configured.

The dropping electronic device 10 is activated upon receiving the emission signal. The second receiving antenna 11 for receiving a radar transmission wave, the same correction value as that of the second storage unit 81 and the same A third storage unit 12a in which a combination of elapsed times is stored in advance corresponding to the data index, and after receiving the firing signal from the airborne electronic device 1, the correction value corresponding to the data index and the progress thereof A Doppler frequency correction control unit 13a for reading and outputting a combination of times from the third storage unit 12a, and the radar received by the second antenna 11 based on the correction value output from the Doppler frequency correction control unit 13a A modulation unit 14 for correcting the frequency of the transmission wave, an amplification unit 15 for amplifying the output signal of the modulation unit 14, and a transmission antenna 16 for transmitting the output signal from the amplification unit 15 It has been made.

Next, the operation of the configuration of FIG. 2 will be described. First, the operations of the antenna 2, the received wave analysis unit 3, the aircraft sensor unit 4, the first storage unit 5, and the Doppler frequency calculation unit 6 are as shown in FIG. Operation is the same as

Then, the determination section 82 stores the information in the second storage section 81
From the combination of the correction value for correcting the Doppler frequency of the dropping electronic device 10 and the elapsed time thereof,
Further, by the relationship between the combination of the correction value and the elapsed time and the combination of the Doppler frequency and the elapsed time from the Doppler frequency calculator 6, the tracking can be shifted from the frequency of the aircraft viewed from the radar in the same manner as described above. It is determined whether or not a predetermined condition is satisfied, and the data index of the combination of the correction value and the elapsed time when the predetermined condition is satisfied is read out from the second storage unit 81 and output.

This data index is sent by the firing control unit 7 to the dropping electronic device 10 together with a firing signal.

The dropping electronic device 10 also starts operating by receiving a firing signal, and the Doppler frequency correction control unit 13a inputs the data index from the airborne electronic device 1, and based on the data index, a third data index. The same combination of the correction value and its elapsed time as in the second storage unit 81 is read out from the storage unit 12a and output.

The modulator 14 corrects the frequency of the radar transmission wave received by the second antenna 11 based on the correction value output from the Doppler frequency correction controller 13a. After amplifying the output signal, the signal is transmitted from the transmission antenna 16.

Thus, the airborne electronic device 1 may transmit a data index to the dropping electronic device 10 instead of the combined data of the Doppler frequency and the elapsed time, and the amount of data to be transmitted can be reduced. .

It should be noted that the predetermined condition in the present invention [1] and [2] is that the time at which the Doppler frequency corrected by the modulator 14 replaces the frequency of the aircraft viewed from the radar is within a certain time range. The slope of the corrected Doppler frequency can be within a certain range.

A data address can be used as the data index.

Further, the Doppler frequency correction control unit 13 in the present invention [1] can read out a plurality of combinations of the correction value and the elapsed time satisfying the predetermined condition from the second storage unit 12 and output them. Further, the emission control unit 7 in the present invention [2] can transmit the emission signal when receiving a plurality of data indexes.

As a result, a plurality of Doppler frequency correction values are given to the modulating unit 14, and a plurality of Doppler frequency corrections can be performed by the modulating unit 14.
The correction range of Doppler frequency is widened, and radar transmission wave 2
3, it is possible to correct the error of the arrival direction and the frequency analysis and the deceleration error of the drop electronic device 10.

[0033]

FIG. 3 and FIG. 4 are flow charts showing an operation example of the configuration of the radio wave jamming device according to the present invention [1] shown in FIG. 1. In particular, FIG. An operation example of the electronic device is shown, and FIG. 4 shows an operation example of the drop electronic device. In each of the drawings, the reference numerals assigned to the blocks correspond to the reference numerals assigned to FIG.

1 will be described below with reference to FIGS. 3 and 4. FIG. First, in the operation of the airborne electronic device 1 shown in FIG.
The direction of arrival θ and the frequency f ₀ of the radar transmission radio wave are detected from the reception wave of the radar using the conventional technique. Further, the aircraft sensor unit 4 has an aircraft speed (horizontal speed) V _M and an altitude A _M
And supplies them to the ROM 5 as a first storage unit.

[0035] ROM5 reads the combinations of the flying speed (horizontal speed) V of the elapsed time t and at that time from the launch dropping time of dropping the electronic apparatus 10 corresponding to the altitude A _M and the aircraft velocity V _M.

[0036] Figure 5, there is shown one embodiment of ROM5, this ROM5 an aircraft velocity V _M and the aircraft altitude A
_{When M} is plotted on the vertical and horizontal axes ((1) in the figure) on each intersection, the dropping electronic device 10 as shown in FIGS. (2) and (3) is dropped with respect to the elapsed time t from the time of dropping. The flight speeds V of the electronic device 10 are combined and stored in advance as a set of data. Therefore, the combined data (set data) of the elapsed time t and the flight speed V is stored by the number of intersections, and the aircraft speed V from the aircraft sensor unit 4 is stored.
A set of elapsed time t and flight speed V corresponding to _M and altitude A _M
Is read.

Next, the combination data of the elapsed time t and the flight speed V is given to the Doppler frequency calculation unit 6 and used together with the arrival direction θ of the radar transmission radio wave output from the reception wave analysis unit 3 and the frequency f _0. The Doppler frequency f _d predicted after the release of the release electronic device 10 is calculated according to the following equation.

[0038] Where f _d : Doppler frequency V: flight speed data f ₀ : frequency of radar transmission wave c: speed of light (3 × 10 ⁸ m / s)

The Doppler frequency f _d there is sent to the firing control unit 7 in combination with the elapsed time t.
It is sent to the drop electronic device 10 together with the firing signal. Note that the firing control unit 7 may be a plurality sequentially sent a combination data of the Doppler frequency f _d and the elapsed time t.

As a result, in the airborne electronic device 1, the elapsed time t and the Doppler frequency f _d of the dropped electronic device 10 are obtained from the combination data of the elapsed time t and the flying speed V after the release of the dropped electronic device 10. It is converted into the combination data, that the combination data of the Doppler frequency f _d of the subsequently elapsed time t dropping the electronic device 10 to a firing signal at the launch control unit 7 as shown in FIG. 6 is transmitted to dropping the electronic device 10 Become. Note that the conventional technique disclosed in Japanese Patent Application Laid-Open No. 4-124598 may be used for this firing and dropping.

Next, in the operation of the drop electronic device 10 shown in FIG. 4, upon receiving a firing signal from the airborne electronic device 1, the power is first activated (step 17).
Thereby, the operation of the drop electronic device 10 is started.

[0042] Then, the Doppler frequency correction control unit 13 inputs the combined data of the elapsed time t and the Doppler frequency f _d received from Airborne electronic device 1 in the power-up from airborne electronic device 1.

When the power is turned on, the second storage unit RO
In M12, the Doppler frequency correction data address k (k
= 1 to n) = starting from 1 (step 121), the Doppler frequency correction data f _b corresponding to the address k are sequentially read in conjunction with the elapsed time t after firing dropped.

[0044] Figure 7, there is shown one embodiment of the ROM 12, and a combination of the elapsed time corresponding to the address k t and Doppler frequency correction data f _b is stored, and the elapsed time t in this case correction data f _b are those obtained by experiment or the like value determined by the aircraft velocity V _M and advanced a _M and the radar transmission wave arrival direction θ and frequency f ₀ above.

[0045] That is, as shown in FIG. 8, is f _c Doppler frequency f _d is (Doppler frequency modulated) which corrected Doppler frequency that decreasing the after dropping the electronic device 10 has been fired dropped dropped The value f _b for transmission from the electronic device 10 is stored in the ROM together with the elapsed time t.
12 is stored.

[0046] Then, the Doppler in the frequency correction control section 13, a second combination data and said elapsed time received from the airborne electronic device 1 t and Doppler frequency between the elapsed time t and the correction value f _b read from the storage unit 12 generating a Doppler frequency f _c corresponding to the elapsed time t by a combination data (step 131).

That is, the Doppler frequency f _c corrected (modulated) corresponding to the elapsed time t = the electronic device 1 mounted on the aircraft
Is calculated by calculating the Doppler frequency f _d + correction data f _b .

[0048] Then, the thus Doppler frequency f _c and the elapsed time t is corrected and operation determine whether it satisfies the tracking transfer conditions 1 and 2 below (step 13
2).

[0049] ◎ transition condition 1 Doppler frequency f _c and the aircraft as seen from the radar frequency f _a tracking transition time t _c (radar tracking crossing (see FIG. 8) aircraft after being modulated by the modulation section 14 (The time at which the electronic device transfers to the dropping electronic device 10) satisfies t ₁ <t _c <t ₂ (where t ₁ and t ₂ are set constants) (2). That constant t _1, t ₂ in the condition 1 is the relationship between the frequency f _a of the aircraft as seen from the radar, the characteristic curve of the Doppler frequency f _c of the modulated (linear) may be the extent to which changes in the left and right This shows the allowable range.

◎ Transition condition 2

[0051] That is constant in this condition 2 is a diagram showing an allowable range slope of whether or the extent to which changes in the characteristic curve of the Doppler frequency f _c of the modulated (straight line).

In this way, it is determined from the radar Doppler frequency of the aircraft whether or not the conditions 1 and 2 for enabling the transition of tracking are satisfied. If not, the address is set to k = k + 1 in the ROM 12. update (step 123), obtains again Doppler frequency f _c reads out the correction data f _b corresponding to the new address k + 1 with the elapsed time t (step 131).

When it is found that the above conditions 1 and 2 are satisfied, a firing command is given to the firing device 18 and the address k at this time is given to the ROM 12 with the elapsed time t being "0". However, the elapsed time t is updated by the internal clock Δt for sequentially reading the correction data f _b for each elapsed time t (step 135).

The ROM 12 stores the address k and the elapsed time t.
It reads the correction data f _b corresponding to (step 12
4), which is given to the correction control unit 13.

[0055] Correction control unit 13 updates the elapsed time t of the elapsed time t by updating only Delta] t transfers the correction data f _b to the modulator 14 by Delta] t.

The correction data f _b output from the Doppler frequency correction control unit 13 is sent to the modulation unit 14 and corrects the frequency f _d of the radar transmission radio wave 23 from the reception antenna 11,
The signal is amplified by the amplifier 15 and transmitted from the transmitting antenna 16.

Here, in the case of the embodiment according to the present invention [1], the electronic device 1 dropped from the electronic device 1 mounted on the aircraft
Since the elapsed time t and the Doppler frequency f _d is sent in combination with respect to 0, the data amount increases.

[0058] Therefore, in order to reduce the amount of data, using a data address for a combination of the elapsed time in the present invention [2] t and Doppler frequency f _d.

FIGS. 9 and 10 are flow charts showing the operation of the configuration of the radio wave jamming device according to the present invention [2] shown in FIG. 2. In particular, FIG. FIG. 10 shows an embodiment of the present invention. In each of the drawings, the reference numerals assigned to the blocks correspond to the reference numerals assigned to FIG.

The operation of the embodiment shown in FIG. 2 will now be described with reference to FIGS. 9 and 10.
This will be described with reference to FIG. First, in the operation of the airborne electronic device 1 shown in FIG. 9, the operations of the received wave analysis unit 3, the aircraft sensor unit 4, the ROM 5 as the first storage unit, and the Doppler frequency calculation unit 6 are the same as those of the embodiment of FIG. The same is done.

The elapsed time t and the Doppler frequency f _d output from the Doppler frequency calculation section 6 are sent to the determination section 82. The operation of the determination unit 82 is performed in step 13 in the Doppler frequency correction control unit 13 in the embodiment of FIG.
The same operations as 1 and 132 are performed in steps 821 and 822.

In order to execute steps 821 and 822, steps 811 to 811 of ROM 81 as the second storage section are executed.
814 are executed, of which steps 811 to 81
3, step 12 of the ROM 12 in the embodiment of FIG.
The same operations as in steps 1 to 123 are performed.

[0063] That is, the Doppler frequency correction data address k (k = 1 to n) = 1, starting from (step 811), the Doppler frequency correction data f _b is the elapsed time t and the combination after launch dropped corresponding to the address k sequentially read out to generate a Doppler frequency f _c corresponding to the elapsed time t by a combination data of the elapsed time received from the Doppler frequency calculating section 6 t and Doppler frequency f _d Te (step 821).

[0064] Then, the thus Doppler frequency f _c and the elapsed time t is corrected and operation determines whether they meet the tracking transfer conditions 1 and 2 described above (step 822),
Meets when no updates the address to k = k + 1 in ROM 81 (step 813), corresponding to the new address k + 1 correction data f _b and the elapsed time t
Request again Doppler frequency f _c is read (step 821).

In step 822, the above conditions 1,
2 is found to be satisfied.
In step 814, the address k at this time is read and given to the firing control unit 7. The firing control unit 7 sends the address k to the dropping electronic device 10 following the firing signal as described above.

In the operation of the dropping electronic device 10 shown in FIG. 10, upon receiving a firing signal from the airborne electronic device 1, the power supply is first activated (step 17), whereby the operation of the dropping electronic device 10 starts. Is done.

Then, the Doppler frequency correction controller 13a
Inputs the address k received from the airborne electronic device 1 from the airborne electronic device 1 when the power is turned on.

After confirming the reception (step 13a1), the Doppler frequency correction control unit 13a gives a firing command to the firing device 18 and sets the address k at this time as the elapsed time t with "0" as the third storage. R as part
It is given to the OM 12a in combination with the elapsed time t (step 13a2).

[0069] ROM12a than stored Doppler frequency correction data f _b corresponding to similarly elapsed time t and the address k and ROM 81, the correction data corresponding to the combination of the elapsed time t and the address k of the correction control unit 13a f _b
Is read and sent to the correction control unit 13a.

In the correction control section 13a, the correction data f
_b is transferred to the modulation unit 14, and the elapsed time t is updated by Δt, and the elapsed time t is updated by Δt (step 1).
3a3, 13a4).

The correction data f _b output from the Doppler frequency correction control unit 13a is sent to the modulation unit 14, which corrects the frequency f _d of the radar transmission radio wave 23 from the reception antenna 11, amplifies it by the amplification unit 15, It is transmitted from the transmitting antenna 16.

[0072]

As described above, according to the radio wave jamming device of the present invention, the elapsed time after the launching and dropping of the dropping electronic device corresponding to the speed and altitude of the aircraft in the electronic device mounted on the aircraft and the flight speed at that time And the Doppler frequency predicted after launching and dropping of the dropping electronic device is calculated from the combination of the arrival direction and frequency of the radar transmission wave in combination with the elapsed time, and sent to the dropping electronic device together with the launch signal, After receiving the launch signal from the airborne electronic device, the dropping electronic device activated upon receiving the combination of the previously stored correction value and the elapsed time thereof, the Doppler frequency given from the airborne electronic device, The correction value that satisfies the predetermined condition that enables the transition of the tracking from the Doppler frequency of the aircraft viewed from the radar in relation to the combination of the elapsed time It is configured to correct the frequency of the radar transmission wave received by the drop electronic device, so that the Doppler frequency can be maintained even after launch and drop, and it is possible to prevent aircraft from being tracked by Doppler tracking radar This has the effect that the aircraft is not targeted for attack. Therefore, it greatly contributes to improving the performance of protecting the aircraft from missiles and shells.

The above-mentioned predetermined condition is determined by the electronic device mounted on the aircraft, and the combination of the elapsed time and the correction data satisfying the predetermined condition is sent to the drop-off electronic device as an address of a storage unit storing the combination. The data transfer amount between the electronic devices can be reduced by modulating the frequency of the radar transmission wave received by reading out the combination of the corresponding elapsed time and the correction data from the same storage unit also prepared on the dropped electronic device side. It is possible to greatly reduce it.

[Brief description of the drawings]

FIG. 1 is a block diagram showing a configuration example of a radio wave jamming device according to the present invention [1].

FIG. 2 is a block diagram showing a configuration example of a radio wave jamming device according to the present invention [2].

FIG. 3 is a flowchart showing an operation example of the electronic device mounted on an aircraft in the radio wave jamming device according to the present invention [1].

FIG. 4 is a flowchart showing an operation example of the dropping electronic device in the radio wave jamming device according to the present invention [1].

FIG. 5 is a diagram showing an image of an embodiment of a storage unit (ROM) for obtaining a flight speed of a dropping electronic device corresponding to an elapsed time in the radio wave jamming device according to the present invention.

FIG. 6 is a diagram showing an image of combined data of the elapsed time and the Doppler frequency of the dropping electronic device transmitted from the launch control unit in the radio interference apparatus according to the present invention [1].

FIG. 7 is a diagram showing a relationship between Doppler frequency correction data and addresses used in the radio wave jamming device according to the present invention.

FIG. 8 is a graph showing the operation principle of the radio wave jamming device according to the present invention.

FIG. 9 is a flowchart showing an operation example of an electronic device mounted on an aircraft in the radio wave jamming device according to the present invention [2].

FIG. 10 is a flowchart showing an operation example of the dropping electronic device in the radio wave jamming device according to the present invention [2].

FIG. 11 is a diagram showing an example of usage of a radio wave jamming device according to the present invention and a conventional example.

[Explanation of symbols]

 EA radio wave jamming device 1 airborne electronic device 2 first receiving antenna 3 received wave analyzing unit 4 aircraft sensor unit 5 first storage unit (ROM) 6 Doppler frequency calculating unit 7 launch control unit 10 dropping electronic device 11 second Reception antenna 12, 81 Second storage unit 12a Third storage unit 13, 13a Doppler frequency correction control unit 14 Modulation unit 15 Amplification unit 16 Transmission antenna In the drawings, the same reference numerals indicate the same or corresponding parts.

 ────────────────────────────────────────────────── ─── Continued on the front page (72) Inventor Masao Moriwaki 4-1-1 Kamikadanaka, Nakahara-ku, Kawasaki City, Kanagawa Prefecture Inside Fujitsu Limited (72) Inventor Shigeru Fujisawa 4-chome, Kamiodanaka, Nakahara-ku, Kawasaki City, Kanagawa Prefecture No. 1 in Fujitsu Limited

Claims (6)

[Claims] A radio wave jamming device having an airborne electronic device and a dropping electronic device launched and dropped from the aircraft, wherein the airborne electronic device receives a radar transmission wave.
Reception antenna, a reception wave analysis unit for analyzing the arrival direction and frequency of the radar transmission wave received by the antenna, an aircraft sensor unit for detecting the speed and altitude of the aircraft, and the drop corresponding to the speed and altitude A first storage unit in which a plurality of combinations of the elapsed time after launching and dropping of the electronic device and the flying speed at that time are stored in advance, and the dropping is performed based on the combination of the elapsed time and the flying speed and the arrival direction and frequency of the radar transmission wave. A Doppler frequency calculation unit that calculates the Doppler frequency predicted after the launch and release of the electronic device in combination with the elapsed time,
A launch control unit for sending a combination of the Doppler frequency and its elapsed time together with a launch signal to the launch electronic device, wherein the launch electronic device, which receives and activates the launch signal, receives a radar transmission wave A second storage unit in which a plurality of second reception antennas and a plurality of correction values for correcting the Doppler frequency of the drop electronic device are stored in advance in combination with an elapsed time after launch and release; After receiving from the onboard electronic device, the combination of the correction value and its elapsed time is sequentially read out from the second storage unit, and the radar is determined by the relationship with the combination of the Doppler frequency and its elapsed time given from the airborne electronic device. A Doppler frequency correction control unit that outputs the correction value satisfying a predetermined condition that enables a transition of tracking from the Doppler frequency of the aircraft viewed from the user, and the Doppler frequency correction control unit A modulator that corrects the frequency of the radar transmission wave received by the second antenna based on the correction value output from the amplifier, an amplifier that amplifies an output signal of the modulator, and an output signal from the amplifier. A radio wave jammer comprising: a transmitting antenna for transmitting; and a transmitting antenna. 2. A radio wave jamming device having an airborne electronic device and a dropping electronic device launched and dropped from the aircraft, wherein the airborne electronic device receives a radar transmission wave.
Reception antenna, a reception wave analysis unit for analyzing the arrival direction and frequency of the radar transmission wave received by the antenna, an aircraft sensor unit for detecting the speed and altitude of the aircraft, and the drop corresponding to the speed and altitude A first storage unit in which a plurality of combinations of the elapsed time after launching and dropping of the electronic device and the flight speed at that time are stored in advance, and the dropping is performed based on the combination of the flight speed and the elapsed time and the arrival direction and frequency of the radar transmission wave. A Doppler frequency calculation unit that calculates the Doppler frequency predicted after the launch and release of the electronic device in combination with the elapsed time,
A second storage unit in which a plurality of correction values for correcting the Doppler frequency of the dropping electronic device are stored in advance in combination with an elapsed time after the firing and dropping, and the correction value and its progress are stored from the second storage unit. The correction value when a predetermined condition for enabling the transition of the tracking from the frequency of the aircraft viewed from the radar in relation to the combination of the Doppler frequency from the Doppler frequency calculation unit and the elapsed time is sequentially read out from the time combination. A determination unit that reads and outputs a data index of the combination of the elapsed time and the elapsed time from the second storage unit, and a launch control unit that sends the data index to the dropping electronic device together with a launch signal. A combination of the second receiving antenna for receiving a radar transmission wave, the same correction value as the second storage unit, and its elapsed time, And a third storage unit in which the correction value and the elapsed time corresponding to the data index are stored in the third storage unit in which the combination of the correction value and the elapsed time is received from the airborne electronic device. A Doppler frequency correction control unit that reads and outputs from the storage unit of No. 3, and a modulation unit that corrects the frequency of the radar transmission wave received at the second antenna based on the correction value output from the Doppler frequency correction control unit. , An amplifying section for amplifying an output signal of the modulating section, and a transmitting antenna for transmitting an output signal from the amplifying section. 3. The apparatus according to claim 1, wherein the predetermined condition is such that the time at which the Doppler frequency corrected by the modulation unit replaces the frequency of the aircraft viewed from the radar is within a certain time range, and the corrected condition is satisfied. Radio wave jammer characterized by the slope of Doppler frequency within a certain range. 4. The radio wave jamming device according to claim 2, wherein the data index is a data address. 5. The Doppler frequency correction control unit according to claim 1, wherein the Doppler frequency correction control unit reads out from the second storage unit a plurality of combinations of the correction value and the elapsed time satisfying the predetermined condition. A characteristic radio jammer. 6. The radio wave jamming device according to claim 2, wherein said emission control section transmits said emission signal when receiving a plurality of data indexes.