The rocket of long range R -33 is equipped only with radar homing head. It is designed for the multichannel guidance, it was developed exclusively for the destroyer, which has on board PHASED-ARRAY RADAR, which permits implementation of a semi-active guidance of several missiles at several targets simultaneously. In this case homing each of the released rockets is carried out in the intermittent duty, since the illumination of purposes is achieved consecutively, moreover the part of time is expended on the retention of survey and the organization of the target of new lock-ons.
Semi-active RGS of rocket R -33 is equipped with the calculator, which forecasts the angular velocity of the line of sighting, analogous established in the rocket R-24R calculator the model of the kinematic relationships of relative motion - initial conditions (relative distance, rate of closure and the projection of the angular velocity of range line) in the flight mission are obtained.
The special feature of the calculator of rocket R-33, in contrast to the calculator of rocket R-24R, lies in the fact that it begins its work from the moment of the end of finalizing with the stabilization system of starting disturbances. Therefore rocket flight to the moment of switching on of calculator must lead rocket into the predetermined point, and on board the destroyer must be calculated the estimations of distance, rate of closure and angular velocity of range line after 2 sec afterward the gathering. Initial antenna position (angular aim designation) also must be forecast on the carrier aircraft before the launching at the moment indicated.
In the process of rocket flight to the seizure the orientation of antenna is determined by the estimations of the angular velocity of range line, manufactured by calculator taking into account the current measured transfer of rocket. The formation of the given g-force is determined by the same estimations of angular velocity.
In the head the indicator gyrostabilizer, built on the base of the sensors of angular velocity, is used. The target lock-on by self-homing head can occur after third of the flight time of rocket. This is reached, in particular, because of the high accuracy of the evaluation of the angular velocity of the line of the sighting BRLS of the carrier (error they are 0,01… 0,03 deg/s).
Doppler self-homing head is characterized by strict agreements of all taking place in it processes with the intervals of the illumination of the assigned for it purpose, equal to 20 ms. In the period indicated is produced the target search in the frequency, and in the process of tracking the measurement of frequency detuning and error angle is carried out. All the remaining time to the following interval of illumination head “is closed” for the method and the signals, formed with it, are calculated as a result forecast from the previous measurements.
In the head the method of direction-finding with processing of signal by the two-channel receiver, which realizes the method of the so-called reserved conical scanning with the compensation, is realized. In each channel independent of others as the normalizing devices are used the diagrams ARU. The accuracy of the measurement of the angular coordinates of target by head, including with amplitude jamming [e.g. inverse gain jamming- PMM], approaches accuracy of monopulse system.
The distance of seizure by the head of a purpose of the type Tu-16 is about 90 km, which taking into account inertial guidance to the seizure provides the possibility of launching from distance on the order of 120… 130 km.
Homing system after seizure consecutively has two structures:
From the moment of seizure on the larger part of way the model of the kinematic relationships as the filter of the measurements of the angular velocity (instead of the acceleration of purpose to the entrance of model it will be given a difference in the measurement of angular velocity and its estimation), is used;
then it is built as stationary (locked outline of the angle tracking of head forms the measurements of the angular velocity of the line of the sightings, which are passed through the stationary filter and after multiplication by the measured rate of closure is formed the given g-force).
A certain decrease of requirements for the value of gradient of synchronous error is achieved because of the application of a negative speed feedback of a change in the angle of deflection of antenna.
Rocket R-33 is built according to normal diagram. Its construction is traditional, and the layout and the aerodynamic shapes influenced the need for the conformal suspension of rocket under the fuselage of aircraft MiG-31.
The characteristics of the rocket of long range R -37 and of its system for control are better than rocket R-33: above located overloads, the permissible launching ranges, noise protection, especially with the guidance to the low-flying and multiple targets.
Rocket R-37, mainly due to a certain increase in power-weight ratio and considerable increase in the time of the work of power unit, fundamentally new construction of control system, provides the possibility of launching from the distance of more than 300 km.
Rocket can be used both from the modernized destroyer MiG-31 and from the destroyers Su-27, Su-35 with the condition of the modification of their software.
CONOPULSE is a hybrid angle-tracking system combining
monopulse and conical scan techniques. Two squinted beams
are rotated or nutated in space in a conical scan manner. The
received signals are processed either with monopulse processing
followed by conical scan or vice versa. The advantage
claimed for the conopulse technique is that, like monopulse,
amplitude fluctuations do not affect the angular accuracy,
while only two receivers are required instead of three used in
a conventional monopulse tracker. With modern solid-state
technology, it can be easier to realize the third receiver than to
arrange proper scanning of a pair of squinted beams. Sometimes
conopulse is called scan with compensation.
Two methods are usually used for angle-tracking radar. They are monopulse and conical scan. The former is free from target-signal amplitude-fluctuation effects but requires multi-channel receiver equipment. The latter requires only one channel but is affected by target-signal amplitude-fluctuation effects. A method is proposed in this paper, conopulse, which combines the advantages of both. Conopulse requires only two channels, and is free from the signal disturbances to which conical scan is subjected. Its main disadvantage is its lower data rate.
Monopulse (Fedosov's book).Dilbert said:So, according to this book (and briefly not to go too far off-topic), what is RVV-AE? Inverse conical-scan, or monopulse?
i think you are right. There is no mention about monopulse in describtion of missile modernization(R-33>R-37) in Fedosov's book.Note that the original R-37 seeker seems to have the same antenna as the R-33 seeker, implying it also uses conopulse?
Dilbert said:For a western antenna designer, this is quite something to see... It appears that for twenty years, USSR managed to develop and produce EVERY antenna technology under the sun, no two alike... except the slotted array.
the MFBU could be pretty common abbreviation, describing blocks on the aircraft, probably he is mixing up two different things.overscan said:Yefim Gordon does mention MFBU-410.
He seems to think its an onboard system of the MiG-31. According to him, it stands for MnogoFoonktsionahl'nyy Blok Oopravleniya or multifunction missile control module. 410 is the R-33 (Izdeliyie 410).
Pit said:In a side note:
It's interesting to know what happened to the K-37M program once slatted as "winner" of the Russian Long Range contest for ALRAAM missiles instead of KS-172 (russian version, range up to 400km)...seems to be superceeded by other developments.
You mean that the KS-172 and R-37 were ompetitors at one time?