DE3334758A1 - Method for combating helicopters with guided missiles - Google Patents

Abstract

The invention discloses a method for combating concealed battle helicopters by means of a guided missile which is equipped with acoustic sensors, its trajectory being divided into a driven ascent phase 2 and into a driveless nosedive-like homing phase 4. The guided missile is fired from a launching device 1 and is driven in the ascent phase 2 by a rocket motor. The burn-out 3 is followed by a driveless nosedive-like homing phase 4, whilst the guided missile is guided into the target by the characteristic sound spectrum of the battle helicopter 5 which it continuously locates acoustically. <IMAGE>

Description

description

Helicopter inheritance fighting method with guided missile he invention is based on a procedure for combating attack helicopters in cover by a guided missile equipped with a warhead from above, the The flight path of the guided missile in a climb phase and a dive-like search phase is divided.

Such a procedure is by the German Offenlegungsschrift- OS 2904749 became known.

In the known case, the guided missile is from launch to target powered and can be used with both active and passive radar or infrared homing heads be equipped.

Guided missiles of this type have the major disadvantage that they are due to their complex construction very costly and, moreover, easy due to simple Means are disruptive. Using passive or active radar or infrared sensors is also an exact location of a certain target object, such as the attack helicopter here, not possible, as these systems only receive the signals integrally (surface retention) can.

The invention is based on the object of a method for combating of attack helicopters in cover to show which with simple Means.

is able to accurately and safely that the attack helicopter from Guided missile is hit.

The task is based on the features of the generic term of Claim 1 solved by its characterizing features.

Through the use of an acoustic direction finding and control system and through a division of the flight phase into a powered and a non-powered (noiseless) for the guidance of a guided missile onto an attack helicopter in cover it is possible to use the attack helicopter without direct visual contact between the launch base and to capture the target object safely and fight it successfully.

The two inventive features of the acoustic target search and the division of the entire flight phase into a powered and an unpowered one The (noiseless) phase has a number of significant advantages.

So the inventive method allows control after "fire and forget" principle. Since the acoustic target search is also a purely passive one Procedure, the guided missile cannot be located during its entire flight phase. The acoustic principle also makes the guided missile practically immune to acoustic signals Deception measures, as the opponent uses the sound sources used for deception reveals own position. Thus, the hit probability is extremely high. By suitable electronic signal evaluation measures are friend / foe identification possible.

The signal evaluation method used for acoustic cell search is in addition, able to different acoustic frequency spectra from each other to distinguish.

It is thus possible for the guided missile to target the combat helicopter int its due to the support rotor and rear rotor running at different speeds evoked characteristic frequency spectrum of sound levels of other frequencies to distinguish.

The design of the flight phase is also positive for the procedure into a driven and a particularly advantageous non-drive phase, which can also be referred to as gliding or search phase.

The acoustic direction finding and control system becomes due to the non-propulsion phase no longer disturbed by the sound of the rocket motor, the remaining intrinsic sound due to the wind flow is so small that it does not affect the acoustic localization.

The guided missile is also practical in the dive phase locatable, as it discards the metallic drive part after the first section of the path can, and thus almost only non-metallic material flies on. Also the optical perceptibility should be with the small dimensions of the rest of the guided missile be very small.

Due to wind and temperature changes depending on the altitude A beam curvature arises above the ground, which the sound energy to the Leads the observer towards (good audibility) or distracts them away from the observer (poor audibility). However, this influence is essentially only for sound propagation on the ground effective and often leads to anechoic zones there. For spreading upwards However, the wind is almost irrelevant, as there is only a curvature of the rays, but not a completely anechoic zone can arise, this is what is proposed in the case of the one proposed Guided missile made use of.

Based on an embodiment shown in the drawing the invention is to be explained in more detail.

FIG. 1 shows a battle picture with the basic principle of the invention Process Figure 2: The missile schematically Figure 3: Block diagram of the electronics, of the acoustic direction finding and control system FIG. 1 shows a launching device 1, which can be mobile, portable or permanently installed. Through this Launching device 1 should be the target. in this case an anti-tank helicopter 5, which has taken cover behind a riser.

A direct line of sight between the launcher 1 and the Anti-tank helicopter 5 does not exist.

The trajectory is shown roughly schematically. It starts with the Ascent phase 2, during which the guided missile is driven by means of a rocket motor will. It drives the guided missile up to a height 3, which is well above the usual altitude of the anti-tank helicopter 5 in cover. The rocket motor is now designed in such a way that it reaches the culmination point after a certain time 3 the trajectory switches off as a result of burnout. To locate the guided missile To prevent a subsequent non-powered sliding phase 4, the Rocket motor blown off if necessary. With the acoustic now switched on The direction finding and control system is the guided missile on the anti-tank helicopter 5 guided by the characteristic frequency spectrum emanating from it.

The base frequency of the carrier rotor is in the range of 10 Hz, that of the Tail rotor in the range of 100 Hzb The warhead is ignited by evaluation the amount of the sound amplitude. It is concluded that there is sufficient approximation, that a previously set threshold is exceeded.

Shortly before the target object anti-tank helicopter 5 can possibly also can be switched to a non-acoustic target search method for a more precise one Ensure final approach. These can already be known active target search methods be because at this point a location of the guided missile and a successful one Combat is already impossible because of the small target distance.

The inventive method shows that the anti-tank helicopter is completely at the mercy of the approaching guided missile. The cover behind that Hill, which safely protects him from ground-based weapons such as guns, tanks, etc., is useless here because the guided missile fights it from above.

The guided missile is also equipped with a friend-foe identifier. Does he recognize the anti-tank helicopter to be fought based on the circumstances Main rotor to tail rotor frequencies as its own so he can make an evasive movement execute and prevent the ignition of the warhead.

Figure 2 shows the missile schematically in plan view. On his Front is a warhead 6, which is known with a proximity fuse Type is equipped. An electronic part 10 is attached to the warhead 6 of the missile, which converts the recorded bearing signals into control signals implemented for the steering device.

The missile is at least three evenly distributed around the circumference Wings 13 provided, at the ends of which are the installation locations for the microphones 7, 8, 9 are located as acoustic sensors.

The tail of the missile is also provided with at least three rudder fins 11, which effects its control around two axes. Wings 13 and Rudder fins 11 can also be combined. A rocket engine provides the drive with nozzle 12.

The missile can be set up so that after burnout of the rocket part this is dropped.

Then the guided missile folds the wings 13 and rudder fins 11 and goes into a nosedive, unpowered search phase, with the helicopter The guided missile is continuously located acoustically by means of the rudder fins 11 is steered towards the goal. There will also be an assessment of those carried out by the helicopter characteristic sound signals, in particular the amplitudes and frequencies of the support rotor and the tail rotor and their relationship to one another, to Freund / Fe ind identification and proximity ignition.

If the helicopter belongs to its own associations, that will Impact of the guided missile prevented.

With the possibly additional final approach device, the guided missile finally steered into the target where the warhead 6 ignites.

FIG. 3 shows the electronics 10 together with the transducers and actuators which is required to steer the missile. The transducers are on the left to see which are represented by the same microphones 14-17 and a pitot tube 24 are. The microphones 14-17 are each connected to a signal processor 18. The signals emanating from the Pitot tube 24 are, after passing through a Doppler corrector 25 is also passed to all signal processors 18. To the assembly the signal processors 18 are followed by two correlators 19 and a warhead igniter 20, the latter being connected to the warhead 6. Two control variables follow to control the transverse and vertical axis 21, which their signals to the servomotors 23 for the missile's elevator and ailerons. Is fed to you also a signal from a steering axle position controller 22.

The electronic device described in this way works as follows: The microphones 14-17 pick up ambient sound and process the sound signals in electrical in a manner known per se. The impulses obtained in this way are sent to the Signal processors 18 forwarded, each microphone 14-17 on its own Signal processor 18 is working.

Figure 1: trajectory 1) launcher, mobile or portable 2) ascent phase with rocket drive, rough directional attitude 3) Burnout or partitioning of the drive 4) Gliding phase controlled by acoustic sensor 5) Target (helicopter) figure 2: missile, schematic 6) warhead 7) 8) microphone pair 9) microphone of the second Microphone pair 10) Electronic part of the missile 11) Rudder fins for control around two axes 12) Nozzle of the rocket engine 13) Airfoils Figure 3: Block diagram of the electronics 14) Pitot tube for speed measurement 15) Derivation of the Doppler shift 14) 15) Microphone pair 16) 17) Microphone pair 18) Signal processors 19) Correlator 20) Warhead igniter 21) Control variable for transverse and vertical axis steering axis position controller 23) Servomotors for elevator and ailerons 24) Pitot tube 25) Doppler correction 26) -Should however, if there are only three microphones on the missile, they would be one experience vectorial combination, which then also like the phase difference can be further processed. The further processing of these two quantities exists in that they are each also in correlator 19 in a corresponding angle information be converted. This Tefinkel information is then sent to the control unit forwarded for the transverse and vertical axis 21, which in turn these signals after Pass on appropriate processing to the servomotors for elevator and ailerons -23.

The amplitude spectrum suffers due to the relative speed a frequency shift between the target and the missile known as the Doppler effect will. Since this phenomenon is very detrimental to the guidance of the missile, it must be corrected. The Pitot tube 24, which determines the airspeed, is used for this purpose of the missile measured relative to the surrounding air and from this the associated frequency shift calculated.

A correction signal is generated with the help of the value determined in this way and passed on to the signal processors 18. This can reduce the Doppler shift can be approximately reversed.

The warhead igniter 20 evaluates the mean amplitude spectrum which is fed to it by the signal processors 18. Upon reaching a The threshold value is deduced from the approach to the target and the ignition process triggered and to the effect that the ignition pulse is sent to the warhead 6 will.

The position control of the missile with respect to its longitudinal axis is through Gyroscopic elements or components that allow the evaluation of the earth's magnetic field, performed. This process takes place in the longitudinal axis position controller 22.

Figure 1: trajectory 1) launcher, mobile or portable 2) ascent phase with rocket drive, rough directional attitude 3) burnout or shearing of the drive 4) Gliding phase controlled by acoustic sensor 5) Target (helicopter) fluorine 2: missile, schematic 6) warhead 7) s) microphone pair 9) microphone of the second Microphone pair 10) Electronic part of the missile 11) Rudder fins for control around two axes 12) Nozzle of the rocket engine 13) Airfoils Figure 3: Block diagram of the electronics 14) Pitot tube for speed measurement 15) Derivation of the Doppler shift 14) 15) Microphone pair 16) 17) Microphone pair 18) Signal processors 19) Correlator 20) Warhead igniter 21) Control variable for transverse and vertical axis 22) Steering axis position controller 23) Servomotors for elevator and ailerons 24) Pitot tube 25) Doppler correction 26) - - blank page -

Claims (10)

Claims 1. A method for combating covered areas Combat helicopters by a guided missile provided with a warhead (6) from above, with the flight path of the guided missile in a climb phase (2) and a dive-like search phase (4) is divided, characterized in that the Guided missile during the search phase (4) is unpowered (low-noise) and by means of one having acoustic sensors installed in / on the guided missile, to which Characteristic sound spectrum of the attack helicopter set direction finder and control device (7-9, 24, 10, 23) can be guided to the target. 2. The method according to claim 1, characterized in that the from Combat helicopters emitted special sound characteristics is filtered out. 3. The method according to claim 2, characterized in that the sound evaluation taking into account the Doppler effect at the respective speed of the Guided missile takes place. 4. The method according to claim 2 or 3, characterized in that the Received sound characteristics evaluated in addition to friend / foe detection will. 5. Guided missile to carry out the method according to -at least one of the claims 1 to 4, characterized in that the missile is a rudder (11) and at least two equal-angularly offset wings (13) has, at the outer ends of the sound receiver and pressure receiver (7, 8, 9, 24) are arranged as sensors of the direction finding and control device, which are connected to a downstream Electronics part (10) are connected, which in turn is connected to actuating devices (23) for the rudder (11) of the missile is connected. 6. guided missile according to claim 5, characterized in that the DF device an electronic signal processing for filtering out a given Has sound characteristics (line spectrum). 7. guided missile according to at least one of claims 5 to 6 characterized characterized in that the electronic part (10) evaluates the signals from the sensors Fourier analyzer contains the Doppler effect compensated on the input side, its The output signal is compared in a correlator (19) with the nominal value and that the target bearing through stereophonic evaluation of the signals received from the sound the one wing (13) compared to the sound receiver of the other wing (13) is feasible. 8. guided missile according to at least one of claims 5-7, characterized characterized in that a position stabilization acting on the rudders (11) of the missile about a longitudinal axis of the missile, e.g. B. gyro device is provided. 9 guided missile according to at least one of claims 5 - 8, characterized characterized in that it is inen warhead (6) with an acoustic proximity fuse having. 10. guided missile according to at least one of claims 5 - 9, characterized characterized as having a rocket engine.