Method of striking target producing coherent interference with missiles fitted with active radar seekers

FIELD: physics.

SUBSTANCE: method of striking a target producing coherent interference by launching and guiding missiles fitted with an active radar seeker involves emitting a probe signal and receiving the signal reflected by the target, wherein two missiles are simultaneously directed onto the target, and emission of the probe signal and reception of the signal reflected by the target are reassigned between the missiles alternately; before launching missiles, the intervals for emitting probe signals and receiving reflected signals are synchronised such that intervals for emitting the signal of one missile match intervals for receiving the signal reflected from the target of the other missile. Switching intervals for emitting the signal and receiving the reflected signal is carried out with frequency higher than the bandwidth of the guidance system, and the frequency of switching emission and reception intervals is set primarily alternating. The missiles are guided into the target on "pliers" type maximally divergent trajectories.

EFFECT: improved method.

4 cl, 2 dwg

 

The invention relates to the field of aviation armament, in particular to methods guidance guided missile of class "air-to-air active radar homing to hit targets Directors active coherent interference, mainly aircraft jammers.

There are various ways to defeat targets by hovering over them with guided missiles and missile guidance system, implement, such as described in [1, 2, 3]. Currently, the most common of these methods is taken as a prototype active radar homing missiles [1], the distinguishing feature of which is that the source of the probing signal and the receiver reflected from the target signal are aboard the guided missile. Such a construction ensures fulfillment of the basic requirements for modern control systems aircraft armament - autonomy missiles in the guidance process, i.e. the implementation of the principle of "launch and forget".

When implementing radar homing direction at the target, the information which is needed to generate control signals missile is determined by the angular discriminator guidance systems. However, since the radar goniometric system determine the direction of the radiation source (in this case on purpose, as the source of the reflected signal as a position normal to the phase front of the radar waves that characterize the situation of some of the effective center of reflection [4], the distortion of the wave front (with respect to spherical) lead to measurement errors, including abnormal. Such distortion of the front and the corresponding measurement error can be either of natural origin due to the specific nature of the reflections, and to have artificially organized. As shown in [4], simultaneous radiation from several sources on a single frequency radar perceives as the radiation from some effective center, the location of which in General does not coincide with any of the real sources.

Organized noise, leading to distortion of the phase front and the evolving purpose of the jammer by radiation from multiple points (minimum of two) correlated to the amplitude and phase of signals, called coherent. The impact of such interference on radar guidance system leads to unacceptable errors and to reduce the probability of hitting a target down to zero.

In particular, if the signal amplitude of the two disturbances emitters E1and E2approximately equal, and the phase shift at the point of reception is close to 180°, the effective centre covered by the Oia will lie outside the base L (where L is the distance between the emitters installed at the ends of the wings), i.e. outside of the path goals. Since putting on radar measurements will be carried out on some of the intangible point of the effective center of the reflection, the real goal is the Director of interference will not be affected. Thus, with proper selection of omahasteaks.com amplitude and phase correlation of disturbances signals the effectiveness of coherent interference is very high and the probability of failure of targeting tends to 1, i.e. the probability of hitting a target tends to 0.

Distortion of the phase front of the radio waves take place when the reflection from complex targets with multipoint nature of the reflection, and are called "angular noise [5]. However, the angular noise is random and abnormal errors, caused by, accompanied by typical goals is acceptable with regard to the filtering properties of the contour guidance. In addition, a sufficiently large number of additional ways to reduce the impact of angular noise, for example in [6], [7]. However, if the distortion of the phase front of the radio waves are not random, and constant targeted, as in the case of the use of coherent fields mentioned above and similar inefficient, and either do not protect against retargeting on the imaginary source or cause blurred aniu circuit controller that eventually leads to the same result - not to defeat the purpose.

However, the possibility of putting coherent interference are fundamental physical limitations, which can be used to protect active radar systems and missile guidance systems with active radar systems. The fact that the region of space in which are necessary for the occurrence of distortion of the phase front phase relationship of the signals of disturbances emitters, due to the difference of progress of radio waves from different points of view is relatively small, and is almost of the order of 0.001 rad angle (or units, or a few tens of meters depending on the distance to a target on linear coordinates).

And if modern means of jamming able to create the required ratio between the amplitudes and phases at the location of the active radar homing head (it discloses its location its radiation), it is already at a short distance from this location required ratios are not met, and distortion of the front are so insignificant that they do not pose a threat. For this reason, coherent interference ineffective against the power, in particular bistatic (i.e. on-off) radar systems, when the probing signal transmitter is in one place, and p is amnic - in the other, and between them there is a significant bistatic angle.

This property of resistance to coherent interference when separated by space transmission and reception, the inherent power systems can be implemented in missile systems with active radar guidance of missiles at the expense of a special organization of the guidance process two missiles and their interaction with each other.

The present invention is directed to solving the problem of increasing the efficiency of defeats the purpose of Director coherent interference by launch and guide missiles with active radar homing.

The problem is solved due to the fact that defeats the purpose of Director coherent interference by launch and guide missiles with active radar homing, including radiation probing signal and receiving a reflected from the target signal, the target shall move simultaneously two missiles, and radiation probing signal and receiving a reflected from the target signal redistribute between missiles alternately, thus before launch intervals radiation probing signals and receiving reflected signals synchronize so that the intervals of the radiation signal one rocket corresponded to intervals of reception of the echo from the target signal other missiles.

In addition, swap the replacement intervals of the radiation signal and receiving the reflected signal is performed with the frequency, exceeding the bandwidth of the guidance system. The switching frequency intervals radiation and reception set variable. This guidance missiles are carried out by the most divergent trajectories of type "ticks".

The proposed method preserves the advantage of active radar system as autonomy, but provides conditions explode in the space of transmit and receive signal, which makes the method is resistant to interference, so that the rocket, which radiates the signal at each point in time and, therefore, potentially exposed to interference of reception does not, and is induced on the basis of measurements made at points in time when she took the signals generated by the radiation of the other missiles. Then the function rockets are changed, and thus, each time the system is similar to the dip of the guidance system with the only difference that the receiver and transmitter periodically reversed.

To ensure continuity of generation of control signals missile proposed switching intervals of the radiation signal and its reception be carried out with a frequency higher than the bandwidth of the guidance system.

At the same time to create additional difficulties in the creation of response interference frequency switching intervals can sadava the change of the variable.

The proposal to implement the guidance of missiles at the most divergent in primary and secondary plots trajectories of type "ticks" is directed to the fact that most of the trajectories of the rockets were furthest from one another and were not included in the region of space in which the effective coherent interference.

The essence of the proposed method is illustrated by the scheme shown in figure 1 and Figure 2.

Figure 1 illustrates the relationship of the interval of emission of the probe pulse single rocket interval of reception of the reflected signal of the other missiles. Figure 2 presents a generalized block diagram of the apparatus of rockets, communication with media, among themselves and with purpose. To implement the method requires additional inclusion of part of the apparatus of missiles, special switches, and the equipment carrier synchronizer for synchronizing the operation of these switches in accordance with their sequence diagram.

So, part of the apparatus of the rocket 1 includes a receiver of radar signals 1.1, the output signals of the angle discriminator which is in the form of estimates of the coordinates of the target are received in the control system of the missile (figure 2 it is not shown), the transmitter 1.2, managed switch 1.3 and transmitting and receiving antenna 1.4 connected through a switch, depending on its condition to the output of the transmitter 1.2 or to the input of the receiver 1.1. In the remaining missiles 2 similarly includes a receiver 2.1, the transmitter 2.2, the switch 2.3 transceiver and antenna 2.4. Part of the equipment of the aircraft carrier 3 also includes a synchronizer 3.1, the outputs of which to launch state clock inputs are connected to the managed switches 1.3 and 2.3, and the signals at the outputs of the synchronizer connected to each of the switches must be in opposite phase.

After the discovery of objective 4 aircraft carrier 3 is generated and transmitted to the missile 1, 2 sequence diagram of the switching modes of delivery-active radar homing of both missiles, their switches 1.3 and 2.3 are synchronized, for example, by filing with the carrier clock pulse out of phase switches on each of the two missiles. After you launch the program switch is remembered and implemented without additional external synchronization. In addition, evaluators missiles (not shown in figure 2) there is a breeding programme for the rockets to the sides of the early and middle parts of the trajectory for the organization in further targeting type "ticks".

After start-up and capture the goal of the jammer is active radar homing of both missiles for each of them alternately creates conditions for determining the coordinates of the target and aiming it for her defeat, because the signal emitted by one missile and the OTP is expressed from the target, accepted by another rocket. However due to the fact that the switching frequency intervals of transmission and reception of signals on each of the missiles is carried out with a frequency that exceeds the bandwidth of the guidance system, the control signal forming missile is the same as in the continuous flow of information.

In the end, on the basis of two missiles with active radar homing is implemented on-off radar system as much as possible (through the use of trajectories of type "ticks") under the terms of the guidance bistatic angle, not exposed to coherent interference.

All of the above regarding the method of application of air guided missile of class "air-to-air active radar homing to defeat the purposes of Directors of coherent interference equally applicable to anti-aircraft guided missiles with active radar homing with the only difference that the synchronizer is included in equipment anti-aircraft missile system.

Sources of information

1. "The basics of radio control" Ed. by Vaatsalya and Vintappare, M.: Owls. Radio, 1973, str.

2. Mwimax, Higashino "Aircraft radio control system" authors, publication vvia. Prof. N.E. Zhukovsky, 1973, p.54.

3. Mwimax, Higashino "Electronic guidance system", M.: Radio and communication, 1982, str-223.

4. "Theoretical foundations of radar systems" Ed. by Aderman, M.: Owls. radio, 1970, p.31.

5. "Handbook of radar". edit Mcconica, M.: Owls radio, 1976, volume 1, str-412.

6. Javadov, "Compensation of errors planetree caused by the distortions of the wavefront", "radio" No. 1, 1986

7. Greene, M., J. Stensby, Radar target pointing error reduction using extended Kalman filtering. JEEE Trans., vol. AES-23, No. 2, 1987, pp 273-278.

1. Way defeats the purpose of Director coherent interference missiles with active radar homing, including radiation probing signal and receiving a reflected from the target signal, wherein for the purpose of carry out over two missiles, radiation probing signal and receiving a reflected from the target signal redistribute between missiles alternately, thus before launch intervals radiation probing signals and receiving reflected signals synchronize so that the intervals of the radiation signal one rocket corresponded to intervals of reception of the echo from the target signal other missiles.

2. The way to defeat according to claim 1, characterized in that the switching intervals of the radiation signal and receiving the reflected signal is implemented with a frequency greater than the width of Polo is s bandwidth guidance systems.

3. The way to defeat according to claim 2, characterized in that the switching frequency intervals radiation and reception set the variable.

4. The way to defeat according to claim 1, characterized in that the guidance of missiles are carried out by the most divergent trajectories of type "ticks".



 

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