DE3033357C2 - Method for the transmission of guidance data to a missile - Google Patents

Description

The invention relates to a method for the transmission of steering data to a steerable Missile mounted on-board receiver by means of a command transmitter outgoing, modulated electromagnetic radiation.

It is known to send the steering data from a command transmitter to the steerable missile by means of wire to transfer. In this context z. B. on the essay "The anti-tank weapon system MILAN" in the magazine "Internationale Wehrrevue", special series 5, 1978, pages 58-62 and on the book by F. Müller "Guide to remote control", Deutsche Radar-Verlagsgesellschaft mbH., Garmisch, 1955, pages 74-76 pointed out. By transmitting guidance data to a missile by means of a steering wire achieved that the target of this missile as little information as possible about the fact of the approach of the flight

body receives

In order to avoid the steering wire, which is undesirable for various reasons, steering data can be created using electromagnetic radiation are transmitted to the steerable missile. This steering method is also described in the last mentioned book by Müller at the place indicated. In doing so, however a receiver attached to the target receives information about the fact of the missile approach. It is true

ίο known to interpret the radio transmission of the commands to the remote-controlled missile as possible so that the enemy is ^{more difficult to recognize this transmission 1} and the effects of opposing interference are reduced as possible. A small transmission power of the command transmitter should be used for this purpose. This transmitter power must, however, be selected to be at least large enough that the useful field strength at the receiver of the remotely controlled missile does not fall below a certain value.This means that during the first time after the missile has taken off, the useful field strength of the command signal is high for its receiver and when the missile approaches towards the goal the disturbance / useful ratio is getting bigger. Since the emitted command transmitter power is kept constant regardless of the respective distance between the command transmitter and the missile and is at least so large that there is a sufficient useful / interference ratio at the target during the entire flight time of the missile, the target can have a received information about the fact of the missile approach for a relatively long time.

From US-PS 29 81 943 is now a radio transmission system between a fixed and a movable Station known, with the receiver of the mobile station from the received signal a signal for the distance between the two stations is derived and with this signal that of the antenna emitted transmitter power is adapted to the current distance. It should each

AO only as much power is expended as is necessary for the respective task in the message transmission. This is to avoid interference from other fixed stations as far as possible. However, this known radio transmission system is not a steering system for the transmission of steering data from a fixed command post to a missile moving away.

The object of the invention is to provide a method for transmitting steering data from a command transmitter to specify a missile, through which the target of this missile as little information as possible about the fact that the missile is approaching is retained, but the fact that it is undesirable for various reasons Steering wire avoided and electromagnetic radiation is used in its place. It should also ensure that the guided missile, which is at the beginning of its flight, has a large shelf to the axis between the command transmitter and the target, from the beginning to the end of its trajectory from the steering signal of the command transmitter is detected.

According to the invention, which relates to a method of the type mentioned at the outset, this object is achieved solved in that the radiation lobe width (divergence angle) of the command transmitter as a function

ei on the distance between the missile and the Command transmitter is controlled so that the receiver in the missile is always just for a sufficient Signal-to-noise ratio required received power

In addition to controlling the beam width of the command transmitter can, according to a development of the invention, also the radiation power of the Command transmitter as a function of the distance between the missile and the command transmitter be controlled so that the receiver in the missile is always just the one for a sufficient signal-to-noise ratio receives the necessary reception power

The divergence angle of the command transmitter is relative in the close range of the missile large and becomes smaller as the distance between the missile and the command transmitter increases. Through this it is also ensured that the guided missile, which is at the beginning a large extension to the axis Kornmandoscnder-Ziel can have, is "captured". In addition, the performance density at the goal will be as close as possible small and also kept the risk of betrayal low.

An advantageous development of the invention provided that the distance-time diagram is known for the missile, is that the control of the beam width and if necessary, the emitted power of the command transmitter is also purely time-dependent. The grain mando transmitter power density can then in the vicinity of the missile, i. H. if the missile is still relatively is close to the command transmitter, be relatively small and increases with increasing distance between the missile and the command transmitter. It will be jo in this context it should be noted that the distance-time diagram for the missile mostly known.

Another useful way of determining the control variable for the club width and possibly the power of the command transmitter is that on a location device connected to the launching system of the missile, z. B. on an infrared goniometer, by means of which the position of the steerable missile is determined relative to the line of sight of the launching system, the intensity of the incoming signal from the missile (IR-S \ gna \) and measured as a signal for controlling the beam width and if necessary, the radiated power of the command transmitter is also used. This measure achieves an optimal adaptation to the weather-dependent attenuation values of the atmosphere.

The transmitter frequency of the command transmitter is advantageously chosen so that there is a high atmospheric Basic attenuation for the electromagnetic radiation emitted by the command transmitter As a result, the weather-dependent "reserve" of transmission power is kept relatively low, so that the otherwise increased risk of betrayal is avoided in good weather conditions.

Claims (5)

Patent claims: 1. Method for transmitting guidance data to a mounted on a steerable missile On-board receiver by means of a modulated electromagnetic signal emanating from a command transmitter Radiation, characterized in that the radiation lobe width (divergence angle) of the command transmitter depending on the distance between the missile and the Command transmitter is controlled so that the receiver in the missile is always just for a sufficient Signal-to-noise ratio receives the required receiving power. 2. The method according to claim I _1, characterized in that, in addition, the radiation power of the command transmitter is controlled as a function of the distance between the missile and the command transmitter so that the receiver in the missile always receives the power required for a sufficient signal-to-noise ratio. 3. The method according to claim 1 or 2, characterized in that provided that the Range-time diagram for the missile is known, controlling the beam width and, if necessary, the emitted power of the command transmitter is also purely time-dependent. 4. The method according to claim 1 or 2, characterized in that that at a location device connected to the missile launch system, z. B. on an infrared goniometer, by means of which the position of the steerable missile is relative to the line of sight of the launch system is determined, the intensity of the incoming signal from the missile f / ft signal) is measured and used as a signal for the control of the radiation lobe width and, if necessary, also the radiation power of the Command transmitter is used. 5. The method according to any one of the preceding claims, characterized in that the transmission frequency of the command transmitter is chosen so that there is a high basic atmospheric attenuation for the emitted electromagnetic radiation results.