JPH0942899A - Electric wave prohibiting missile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a missile launched from an airplane, radiating a hindering electric wave to an alarm monitoring radar of an enemy and guiding the airplane in which a ban-through range of the airplane is shortened, the airplane is not caught by the radar so as to enable the airplane to approach more near the enemy. SOLUTION: A transmitter 2 is installed on a missile 10. A hindrance electric wave 7 is radiated from an antenna 1 against an alarm monitoring radar 30 and then an airplane guiding electric waver 8 is transmitted to an antenna 6 through an airplane guiding electric wave cable 5. The electric wave 8 is sent to an airplane 20 so as to guide the airplane 20. An inertia device 3 provides a predetermined steering instruction signal through a cable 4 so as to cause the missile 10 to fly by inertia toward a target. The missile 10 is launched from the airplane and the airplane may fly in such a way that a difference in orientation between the guiding electric wave 8 and a searching electric wave radiated from the alarm monitoring radar 30, resulting in that it is possible to shorten a ban-through range of the airplane, cause a catching of the airplane through the radar 30 to become difficult and further enable the airplane to approach near the enemy.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a jamming vehicle which outputs a jamming radio wave to a warning and control radar and outputs a guidance radio wave to a rear aircraft.

[0002]

2. Description of the Related Art FIG. 9 shows a conventional flight condition of an aircraft using jamming radio waves and shows a self-screening gemer system. In the figure, the aircraft 40 is equipped with equipment for electromagnetic interference under the wings, emits an interference radio wave 41 to the warning and control radar 30, interferes with the radar detection radio wave 31 emitted from the warning and control radar 30, and detects the radar detection ability. Lower.

FIG. 10 also shows a conventional flying state of an aircraft using a jamming radio wave, and shows a stand-off jammer system. In the figure, a jammer machine 50 equipped with a jammer pot radiates a jamming radio wave 52 to a warning / control radar 30 from a remote place in order to support an ally attack machine 51, and a target warning / control radar 30 It interferes with the radar detection radio wave 31 that is emitted and reduces the radar detection capability.

[0004]

In the above-described conventional method of radiating interference radio waves and flying, when an aircraft approaches the target alert control radar 30, a band-through (reception of radar radio wave reflection from the aircraft interferes). (A distance larger than the reception of electric power) occurs, and the aircraft is discovered by the warning and control radar 30, and is tracked and captured.

FIG. 11 is a view showing the state of this bun-through. As shown in FIGS. 9 and 10, aircraft 40 and 50 are radiating ECM radio waves to the enemy's warning and control radar 30, and are flying. Assuming that the distance from the radar 30 is R, the vertical axis represents the received power of the warning and control radar and the horizontal axis represents the distance. In this figure, the radio wave from the radar 30 is reflected from the aircraft 40, and the electric power 53 received by the radar 30 and the received electric power 54 of the ECM (jammer) signal are respectively the received electric power 53 of 1 / R ⁴ and the received electric power 54. It changes with 1 / R ^2, and the received power increases as the distance decreases. Received power 5
When the distance is smaller than the intersection 55 with 3, 54, the reception power 53 of the radar reflected from the aircraft 40 becomes larger than the reception power 54 of the jammer signal, and the aircraft 40 is captured and tracked by the warning and control radar 30. .

According to the present invention, the above-mentioned band-through range is made smaller so that the aircraft can be brought closer to the enemy's territory. It is intended to provide a radio-interference flying body that makes it harder to be disturbed.

[0007]

Therefore, the present invention is provided with an interfering radio wave radiating means and an induced radio wave radiating means, which are emitted from an aircraft and fly in front of the aircraft according to a program previously input before the launch. In addition to adding radio interference while radiating jamming radio waves to the enemy's warning and control radar, it also shows the range of jamming by radiating guidance radio waves to the aircraft, making it easier for the aircraft to enter. Providing a characteristic jamming spacecraft.

In the radio interference vehicle of the present invention, the position of the warning and control radar, which is the target, is given in advance as an initial value by the above-mentioned means, and is emitted from the aircraft toward the target ahead. In accordance with this initial value program, the flying body performs inertial guided flight in front of the aircraft by the onboard propulsion device, and while flying, in the front of the aircraft, jamming radio wave emission means, such as a radio wave transmitter, causes a disturbance of a predetermined power level. Radio waves are continuously emitted to the target. Further, the flying body outputs this interference radio wave to the target, and at the same time, to the aircraft on the rear side by inductive radio wave radiating means, for example, radiating the induction radio wave from the radio wave transmitter from the rear antenna of the flying body. It continuously emits the induction wave of.

The aircraft in the rear receives both the guide radio wave and the detection radio wave radiated from the warning and control radar, and calculates the azimuth difference between the radio waves by a signal processing device, for example. Aircraft pilots fly to eliminate this heading difference,
Since the flight is carried out behind the flying body so as to eliminate the heading difference of the warning and control radar, it becomes difficult for the warning and control radar to capture an aircraft flying behind the flying body. In addition, since the flying object emits jamming radio waves and the aircraft flies behind it, the bun-through range is shorter than the bun-through range by the conventional self-screening jammer. can do.

[0010]

Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 is a configuration diagram of a radio wave interference flying vehicle according to an embodiment of the present invention, and FIG. 2 is a timing chart of radio waves emitted from the flying vehicle. In these figures, 10 is a flying object,
1 is an antenna, 2 is a radio wave transmitting device, 3 is an inertial device, 4
Is a steering signal cable, 5 is an aircraft induction radio wave cable, 6
Is a rear antenna, 7 is an interfering radio wave emitted from the antenna 1, and 8 is an aircraft induction radio wave emitted from the rear antenna 6.

FIG. 3 is a block diagram of an aircraft flying behind the flying object 10 shown in FIG. 1, and FIG. 4 is a timing chart of radio waves received by the aircraft. In these figures, 20 is an aircraft, 21 is a radio wave receiver, 22 is a received signal processing device, and 23 is a receiving antenna.

In the configuration shown in FIGS. 1 to 4 described above,
The flying body 10 is emitted from an aircraft and flies in front of the aircraft. The transmitting device 2 transmits an interference radio wave 7 to the antenna 1 and an aircraft induction radio wave 8 to the rear antenna 6, respectively. By outputting the jamming radio wave 7 from the antenna 1 to the warning and control radar 30 described later, the position cannot be recognized.

The target position of the flying object 10 is given as an initial value before flying, and the position of the warning and control radar 30 commanded by the aircraft 20 is set by the inertial device 3 and the signal cable 4 for issuing a steering command. Inertial flight toward. The aircraft guidance radio wave 8 generated by the transmission device 2 is supplied to the rear antenna 6 via the aircraft dielectric wave cable 5, is output from the antenna 6, and guides the rear aircraft 20 shown in FIG.

The timing chart of FIG. 2 shows the antenna 1
6A shows the timing of the radio wave output from the rear antenna 6 and (a) shows the interfering radio wave 7, which constantly outputs a constant level of electric power in order to prevent the warning and control radar 30 from recognizing its position. (B) shows an aircraft guidance radio wave 8, and since the radio wave 8 guides an aircraft 20 flying behind,
Guided radio waves are output at timed intervals.

In the aircraft 20, as shown in FIG. 3, the receiving antenna 23 receives the radio waves radiated from the warning and control radar 30 and the aircraft guidance radio waves 8 radiated from the rear antenna 6 of the flying body 10, and receives them. Machine 21. The two received signals are input from the receiver 7 to the reception signal processing device 22, calculate the heading difference between the two radio waves received here, and instruct the pilot on the flight heading.

FIG. 4 is a timing chart of radio waves received by the aircraft 20. (a) shows radar detection radio waves 31 emitted from the warning and control radar 30, and (b) shows the rear antenna 6 of the flying vehicle 10. 2 shows the aircraft guidance radio waves 8 radiated from each of them, and the reception signal processing device 22 discriminates both signals from the reception timing of these signals and calculates the heading difference.

FIG. 5 is a diagram showing a state in which the above-mentioned aircraft 20 is flying with a heading difference.
A radar detection radio wave 31 is radiated from the aircraft, the aircraft 10 emits an interference radio wave 7 to the warning and control radar 30, and the aircraft 20 emits a detection radio wave 3 from the radar 30.
1 and the aircraft guidance radio wave 8 emitted by the flying body 10 are received with a heading difference.

On the other hand, FIG. 6 shows a case where the aircraft 20 receives the radar detection radio wave 31 and the aircraft induction radio wave 8 emitted by the flying body 10 without having a heading difference.
As shown in FIG. 6, by flying the flying body 10 so as not to have a heading difference, it becomes impossible to capture the aircraft 20 flying behind from the warning and control radar 30.

FIG. 7 is a diagram showing a bun-through range when the present flying vehicle 10 is used. FIG. 7A is a warning and control radar 3
0, the flying object 10, the arrangement of the aircraft 20, (b)
FIG. 4 is a diagram showing a bun through range in this arrangement state.
In (b), the horizontal axis is the distance, the vertical axis is the reception power at the radar 30, the curve 32 shows the radar radio wave reflection reception power that the detection radio wave radiated from the radar 30 is reflected from the flying object 10, When the distance between the radar 30 and the flying object 10 is R1, it changes by 1 / R1 ⁴ . Curve 33
The interference radio wave radiated by the flying body 10 is the interference radio wave signal reception power received by the radar 30 and changes by 1 / R1 ² .

A curve 34 is the radar radio wave reflected and received power in which the detection radio wave emitted from the radar 30 is reflected by the aircraft 20, and when the distance between the flying body 10 and the aircraft 20 is d, 1 / (R1 + d) ⁴ Change.

Of these curves, the distance B at the intersection of 32 and 33 indicates the band-through range of the flying vehicle 10,
When the distance is shorter than this distance, the radar electric wave reflection reception power becomes larger than the interfering radio wave signal reception power and is detected by the radar 30. This band-through range is the same as the conventional self-screening jammer shown in FIG. Curves 33 and 34
The distance A + d at the point where and intersect the band-through range of the aircraft 20, A is the distance of the flying vehicle 10 at that time, and as is clear from the figure, A + d <B.

As shown in FIG. 7, the use of the flying vehicle 10 shortens the bun-through range of the aircraft as compared with the conventional method, and the aircraft 20 is not captured by the warning and control radar 30 and may penetrate further. it can.

FIG. 8 shows a case where a large number of flying objects 10 are fired. In this way, when a large number of the main flying objects 10 have come in, the alert control radar 30 has a lowered target identifying function in the direction in which the main flying object 10 comes in, and cannot capture the aircraft 20 flying behind.

According to the embodiments described above, (1) the flying body 10 obtains the position of the target warning and control radar 30 from the aircraft 20 as an initial value, and the mounted propulsion according to the program. Inertia-guided flight in front of the aircraft 20 by the device. (2) This flying object 10
Emits the jamming radio wave 7 continuously to the target in front of the aircraft 20 while flying. (3) Flying body 1
0 outputs an interfering radio wave 7 to the target, and intermittently emits a guide radio wave 8 to the aircraft 20 on the rear side.

(4) The aircraft 20 has a reception signal processing device 22.
Then, the two radio waves 7 and 8 are compared, the heading difference is calculated, and the pilot is instructed to do so. The pilot causes the aircraft 20 to fly so that the heading difference is set to "0". The aircraft 20 flying behind the flying object 10 cannot be captured. Further, at this time, the bun-through range of the aircraft 20 is shortened, and the aircraft can be brought into contact with the warning and control radar 30 more.

[0026]

As described above in detail, the radio wave jamming vehicle of the present invention is launched from an aircraft, and it travels in front of the aircraft according to a program previously input before launching, and the jamming radio wave is generated. Equipped with radiating means and guiding radio wave radiating means, while adding radio wave interference to the enemy warning and control radar while radiating jamming radio waves, indicating the range of jamming by radiating guidance radio waves to the aircraft, Since it is characterized by facilitating the entry of an aircraft, the following effects are achieved.

(1) Since the present invention has a shorter bun-through range than the bun-through range of the conventional self-screening jammer, it cannot be captured by the warning and control radar and can penetrate further.

(2) Even if the warning and control radar emits a surface-to-air missile that tracks radio waves, the target is the flying body flying in front of the aircraft, and the aircraft flying behind is It's safe.

[Brief description of drawings]

FIG. 1 is a configuration diagram of a radio interference vehicle according to an embodiment of the present invention.

2A and 2B are timing charts of radio waves emitted by the radio wave interfering flying object shown in FIG. 1, in which FIG. 2A shows a waveform of an interfering radio wave, and FIG.

FIG. 3 is a configuration diagram of an aircraft to which a radio interference vehicle according to an embodiment of the present invention is applied.

FIG. 4 is a timing diagram of radio waves received by the aircraft shown in FIG. 3, where (a) is a radio wave emitted by a warning and control radar, and (b) is a diagram.
Shows the waveforms of the aircraft guided radio waves radiated from the flying objects.

FIG. 5 is a diagram showing a flight state of a radio interference vehicle and an aircraft according to an embodiment of the present invention, showing a case where there is a heading difference between a radar detection radio wave and an aircraft guidance radio wave.

FIG. 6 is a diagram showing a flight state of a radio interference vehicle and an aircraft according to an embodiment of the present invention, showing a case where there is no heading difference between a radar detection radio wave and an aircraft guidance radio wave.

FIG. 7 is a diagram showing a band-through range between an electromagnetic interference flying vehicle and an aircraft according to an embodiment of the present invention, in which (a) is a positional relationship between a warning and control radar, a flying vehicle, and an aircraft;
(B) shows the bun through range in the arrangement of (a), respectively.

FIG. 8 is a diagram showing a state in which an aircraft flies by ejecting a plurality of radio-interfering flying objects according to an embodiment of the present invention.

FIG. 9 is a diagram showing a flight state of a conventional aircraft that emits interference radio waves and shows a self-screening jammer system.

FIG. 10 is a diagram showing a flight state of a conventional aircraft that emits jamming radio waves and shows a stand-off jammer system.

FIG. 11 is a diagram showing a band-through range of a flying aircraft that emits conventional jamming radio waves.

[Explanation of symbols]

 1 Antenna 2 Transmitter 3 Inertial Device 4 Steering Signal Cable 5 Aircraft Guidance Radio Cable 6 Rear Antenna 7 Interference Radio Wave 8 Aircraft Guidance Radio Wave 10 Aircraft 20 Aircraft 21 Receiver 22 Received Signal Processing Device 23 Reception Antenna 30 Warning and Control Radar 31 Radar Detection radio wave

Claims (1)

[Claims] 1. A radar which is emitted from an aircraft and is designed to fly in front of the aircraft in accordance with a program inputted in advance before the launch, and which is provided with an interfering radio wave radiating means and an induced radio wave radiating means, and is used as a radar for warning and control of an enemy. While adding radio wave interference while radiating jamming radio waves, showing the range of radio interference by radiating induction radio waves to the aircraft,
An electromagnetic interference flying vehicle characterized by facilitating entry of the aircraft.