DE2162983A1 - STEERING BODY SYSTEM EQUIPPED WITH TARGET SEARCH DEVICE - Google Patents

Description

Guided missile system equipped with a homing head. Description of the invention Semi-active guided missile systems have the disadvantage compared to active arrangements that the missile on its approach to the target without the application of particular complicated and complex measures neither provide information about the distance that is still present to the goal, still about the relative speed. This information is but important for optimal flight behavior, especially in the final flight phase, e.g. when fighting medium and small sea targets the kill in the area the waterline should be done. Then there would be no need except for one relatively simple contact detonators still very complicated and expensive proximity ignition methods apply. The possibility of interference-suppressing gates for relative speed and distance to target and means for effective target selection or discrimination the object to be fought consists of decoys (decoys, doubles, etc.) only very deprived. In active guided missile systems, the harmful Effects of active opposing electronic countermeasures (ECM) to a large extent thereby eliminate the use of coded or at least varying pulse sequences Signals.

In semi-active systems is for the transmission of position and Path data to the FK by the lighting technician but also the exact knowledge of such data required by the lighting technician. Obtaining such information, however, requires a very large metrological effort.

The beam intensity and concentration must be sufficiently large around the generally very small (with radar the equivalent) reflection value of the rK in the direction of the lighting technician still usable via the interference signals (as well as clutter) to get outstanding useful signals. When chasing several FK (volley shot) each FK would require a separate illuminator bit corresponding selective channel and possibly also a special modulation code, an additional one of its own Burden on logistics. Often, however, the pursuit of an FK is up to the goal Reason for the beam propagation properties (limited visibility due to the curvature of the earth) not be possible at all.

If the operator is no longer on the Connecting line of the lighting equipment to the target (e.g. if the launch system is supported by the starter and / or the target object Carry out any position changes during the FK approach or because of tactical reasons Reasons for deliberately choosing an approach from another direction in order to defend yourself to complicate) so this could be done by means of a complicated one Calculation methods are included in the data entry. But you would Precious computer capacity on board the carrier is used during combat operations unless a special computer is available for each lighting replacement is done, which would significantly increase the effort.

If the FK was equipped with a special transmitter, its azimuth and elevation can be better determined from the lighting technician, so that would be omitted Advantage of the semi-active system, which consists in the fact that the opponent does not have the rK can be located passively. The signals coming from the lighting technician to the FK are used as a reference to preserve the information you want (which is the case when starting a stationary lighting would be possible), the FK needed an additional egg-catching channel with a sensor that is directed towards the illuminator, i.e. towards the rear, if possible. However, this connection is also critical if the FC changes due to the curvature of the surface of the fire is already outside the line of sight of the FK lighting technician. For tactical reasons However, it is often desirable that the FC is as low as possible when approaching the target to fly. In addition, when approaching from a different direction than where you are the lighting technician is during the final flight phase of the FK, measurement error.

The semi-active guided missile system according to the invention adhere the defects just listed do not indicate. There can be several, theoretically any number FK can be brought to the goal independently of each other in a volley shot. This is important for the system design of the 80s, because until then with increased anti-missile activity the opposite side must be expected.

In addition, the ECM effectiveness is likely to increase significantly in 10-15 years and require additional ECCM. That creates the system according to the invention these possibilities by using the location coordinates of the target object directly in the case of FK, i.e. without the aid of coded data transmission methods from the lighting technician can be obtained, regardless of the direction from which the approach is made. There is no natural radiation from the FC. Therefore a location is different Page not possible without active funds. - Noise-suppressing arrangements can be used how gates etc. are used exactly as with the active systems. Want the ECH resistance of the system can also be increased by means of signal coding, see above this is according to the invention by means of a signal rasterization without significant technological overhead achieved. The system according to the invention even permits the change of the target object6 for FK already in the march phase both as well as the handover of the lighting function to other analog lighting equipment z. B. also on separate carriers.

The system design is not based on any particular frequency range bound, deh. The procedure can be used for clear weather (e.g. IR laser) as well as for all weather (with radar) can be applied equally well0 It also makes no difference whether for the Target lighting impulse method with or without coding or whether modulated CW method to be used. Combined arrangements (e.g. clear weather for close range - bad weather for long range) based on common principles the basic components are used.

The functional sequence of the system according to the invention is based on a simple one Example explained. In FIG. 1, only the most important function elements are shown in the block diagram The upper half (a) contains the lighting arrangement, the lower half (b) the arrangement in one of the FK. Before the start there is a connection between the two via the connector K. After the corresponding start-up time of the arrangement in the FK, to the To ensure the required frequency stability, trigger sets Tr der Synchronism between illuminator ~ and FK target seeker device initiated in order to to be perfect at the FK start (separation from K).

The two are essential components of the system according to the invention Frequency standards (here referred to as clock generator TG), which maintain of synchronism with a sufficiently small deviation until the respective FK must guarantee the goal, a condition that, according to the current state of the art Technology for a flight time of 200 sec, for example, with a portable weight and volume requirement (of approx. 1 kg and 1 dm3) can be met.

Here an arrangement was chosen, for example, the impulses for Obtaining the distance information used, as it is used in both laser devices as is also used in radar procedures Via the directional antenna IR of the antenna system A, bundled beams are directed onto the target object. the The transmission frequency or modulation frequency is constant via the transmission oscillator 0 of the clock TG.

The signals reflected from the target reach the receiving antenna RA (which can be identical to the heater) and run (if necessary after separation in the switch H) to the receiving part M2. This contains the necessary elements such as gate circuits for the separation of interference signals, such as decoders, mixer and amplifier stages. Except for the rest of the processing, M2 has additional signal outputs (channels I and II). In channel I, the signals are demodulated in D, analyzed in A2 and stored in 5p2. Then the coding part CG and the raster gate circuit Ra performed pulse control for the transmitter M1. The regularity according to which this timing of the transmission impulses takes place, FIG. 3 shows in a further block diagram FIG. 7a and in an extract of a relay switching diagram FIG. 7b shows the arrangement of the functional elements provided for this purpose. For the sake of clarity, a very simple arrangement of the invention has been used Subject selected as an example. The laws according to which the signal control takes place at the illuminator, diagram show FIG 2 and FIG 3. FIG 5 ni shows the principle temporal functional sequence during a switching period, FIG. 6 shows the same sequence over several periods of the impulse generation: that of the frequency standard by frequency division derived '2 standard impulses "are with the running Arabic numbers 1,2,3,4, 5 .... designated. The constant time interval between two consecutive Pulses are T. The storage device for the distance information was a Arrangement of resistors and capacitors (FIG 7b) selected, assuming that the charging currents across R1, 1 / 2R1, R2, and R2 / 2 are constant in the working range, so that the respective state of charge (EMF) of the capacitances C1 and C2 is proportional the respective elapsed time - FIG 6 shows the relay diagram for U, V, W X and Y. The 5 relays work in an interplay with one another in such a way that the odd pulses from the memory combination (R1 C1) (left) the even-numbered ones Pulses can be controlled by the R2 C2 combination (right).

Although the invention provides for the distance information several average successive impulse groups, especially if a bad one Useful interference signal ratio makes this appear given.

These functions are carried out in the memory arrangement Sp 2 FIG.

The relay works with half the pulse repetition frequency. To switch on and off of the other relays happens depending on the impulses or on the point in time at which the trigger voltage U is exceeded in the memory sets.

The tips Po, P1, P2, P3 and P4 in FIG. 6 each mark the point in time the transmission pulse delivery, where, however, PRo to PR4 mark the point in time at which the return pulse from the illuminated target object arrives at the illuminator.

The markings Zo to Z4 (below) indicate the arrival of the signal pulses at the target object and SO to 84 the arrival at the approaching FK. The interval A therefore illustrates the runtime of the signal from the target to the 7K.

They are the same for the lighting technician and the FC to be controlled by him. The actual code now consists of any one previously used by the lighting technician and the FK Follow-up cycle specified for the total flight time (e.g. from a magnetic storage device).

In the present example, the radiation takes place at the positions 2 - 3 - 5 - 1 - 1 -.

Through this measure, you can (especially on the other side deliberately generated ECM) disturbances largely suppressed and harmless for the FK steering process be made.

JIG 5 shows clearly based on the course of the charge, as with later When the return pulse arrives, the aim of the illuminator is the pulse us half the amount of time is emitted earlier (solid Kur @ enzug @ short distance, dashed Curve = greater distance between illuminator and target).

The signal profile in channel II in FIG. 1a is as follows @: After passing an analyzer A1 is the detected Doppler frequency, which results from the shift of return signal versus transmission signal due to the relative speed of the target illuminator results in the direction of the beam, stored in Bp 1 (e.g. by means of a flywheel oscillator), after that, after passing a frequency shift FS, the modulation of the oscillator takes place 0 generated "standard frequency" in the quiet that the respective transmission or modulation frequency the radiation in IA corresponds to the law according to diagram FIG 2, i.e. the frequencies of the illuminator signals used for the proximity information lie each shifted by half the absolute amount compared to the standard frequency, around which they receive the illuminator signal versus the frequency of the illuminator signals are shifted.

In other words: The frequency control is done in the wise way at all times the standard frequency in the middle between the frequency of the lighting signals and frequency of the reflected signals. In FIG 8 is the frequency control shown in a further block diagram with the most important functional elements. In H, stand is derived from a standard frequency derived from 0 and one from one Frequency converter FU coming frequency 1/2 fd the actual frequency Fe for the Transmit signal processed, which passed via the transmitter E to the directional antenna EA Das Target reflection signal recorded by the sensor RA with the carrier bz.

the modulation frequency fr is amplified in R in a known manner and at the same time provided for the other requirements. With the help of fe the Doppler shift is determined, furthermore a separation of in the decoder DEC Noise signals made. After a backup and, if necessary, formation of a unambiguous, namely the real relative speed information from a series The frequency converter FU is fed with the corresponding measured values Signal.

The control loop is thus closed. To make the measurement method available takes place after a control of the measured values for the distance and relative speed information and if necessary a correction in an integrator in connection with a kl. Computer Cp (FIG is), which forms a cross connection between A1 and A2.

The function sequence for the target seeker of the FK is analogous. He corresponds the way a normal active target searcher works with the difference that the signal reference is taken from the internal signal processing, and that for the determination of the target distance and movement data only the simple path signal propagation time and the simple one Doppler shift are decisive (and not how with active radar the double for outward and return) (FIG 4). At the moment of takeoff was by means of a synchronizer Sy between the signal generators O in the seeker head and illuminator synchronism has been established.

The coding device in the key identical to those of the illuminator (e.g. on mini magnetic tape) were saved using the TR trigger and the Connector K started on schedule. The pulse rasters RA are also synchronized Frequency standard precisely controlled. On the one hand, signal correlation in C the exact distance from the FK to the target j on the other hand the relative speed information FK target object can be determined by determining the Doppler shift.

In doing so, those coming from the lighting technician and those reflected from the target arrive Signals via the search / track antenna STA, the gate circuit TS, the receiving and Amplifier part R to both C and to analyzer A7, where a comparison of the two Types of information and a corresponding mutual correction is made in order for the further signal processing (FK steering and control and, if necessary, ignition release) to obtain optimal surgical data. In addition, the data from A2 is shared of the pulses from CG and Ra rasterized according to the code sequence for an additional effective Interference suppression is also used.

The invention also provides vor1 z. B. over multiple pulses a To carry out transmission of the distance and relative speed information and thus the opportunity to win by controlling the gate circuit and selection the Doppler frequency, a target transmission secured against interferers and, if necessary to be able to change the target after the respective start of the FK.

The system is not tied to a specific frequency range.

Its area of application extends from acoustics to radio technology up to optical transmission technology including lasers.

Claims (7)

Technical features of the invention (Claims) Equipped with with target seeker after the guided missile system operating on the lighting principle, characterized in that both lighting equipment and missiles have clock generators synchronized with one another, of which the time reference for obtaining distance and speed information related to the target object as well as key information for interference suppression is derived. 2) System according to claim 1) characterized in that the temporal Control of the signal output at the lighting technician is carried out in such a way that the Influences from the distance between the illuminator and the target and / or the relative speed Illuminator / target to be eliminated0 3) System according to claim 1) and 2) characterized in that that the signal emission automatically in the manner depending on the target distance and target speed to the lighting location is controlled so that the signals are timed be emitted prematurely by half the amount by which it is delayed as a reflection be caught again by the illuminated target object, and with a frequency shift of the carrier and / or the modulation by half the absolute amount with the opposite Sign as the result of the signal reflected from the target object to the illuminator Experiences Doppler shift. 4) System according to claim 1) to 3) characterized in that after Analysis of the distance and speed information from those in the missile received signals coming from the target object with a computer Measured values are matched to one another and corrected accordingly and that at the same time after appropriate data storage over several measuring cycles, the overall evaluation according to the quality-related weights of the individual measured values for optimal determination the flight path data for the initiation of steering processes and other system-related ones Work functions takes place. 5) System according to claim 1) to 4), characterized in that precautions for a more or less systematic signal coding are taken, with before FK start by a trigger process Synchronism for the code sequence for the lighting technician (s) and missile (s) is manufactured. 6) System according to claim 1) to 5), characterized in that one a precisely defined time grid is provided, within which the temporal position of follow-up pulses in the case of pulse signals (or of time-changing frequency states with other applied modulation types) is fixed, whereby the latitude of this Rasterization is chosen so that ambiguities in the information obtained are excluded are. 7) System according to claim 1) to 6), characterized in that precautions to synchronize the clocks and to maintain this synchronism are provided in the case of several illuminators, for example by transmitting commands in both directions with ongoing correction due to the signal propagation times0 8) System according to Claim 1) to 7), characterized in that a signal correlator is provided, which by means of a computer the own information and that of the lighting technician information about target data that is additionally transmitted in code form with one another compares that after the analysis of the results the correctness of the currently pursued target object is confirmed, or that the selection of a target change new destination, e.g. B. using speed and distance gate circuits, the according to the dictated information about the data of the new target object are regulated, takes place.