Uragan-5B / Smerch / Smerch-A Radars

overscan (PaulMM)

overscan (PaulMM)

Administrator
Staff member
Joined
27 December 2005
Messages
17,755
Reaction score
26,478
Smerch-A radar from Phazotron museum, missiles.ru
 

Attachments

  • smerch-a.jpg
    smerch-a.jpg
    108.1 KB · Views: 875
Looking at the feed of the Smerch antenna is the small upper feed evidence of the "secret" 2 cm "range only" mode for jamming conditions?
 

Attachments

  • smerch feed.jpg
    smerch feed.jpg
    9.2 KB · Views: 780
Courtesy of Crossiathh from ACIG -

You will find some picture of the RP-25 and RP-25M in a video from a russian tv broadcast at

ftp://ftp.redrodgers.com/Video/VoennoeDelo/ (Istorija radarov VVS).
Click to expand...

a short Russian TV documentary on Radar. We get shots of the Phazotron museum, Smerch-A; Sapfir-25 etc.
 
Can somebody find a good picture of a cockpit of the Mig 25 PD. Or a drawing of a cockpit. I need it for Instruments identifications. BTW
here is what I found. Can someone identify the instruments (they are markerd with numbers) assuming that is 25 PD?
 

Attachments

  • mig_25pd_011_cockpit.jpg
    mig_25pd_011_cockpit.jpg
    312 KB · Views: 998
I'm very intrested in both Smerch-A and Sapfir-25 radars.Does somebody has detailed info of them?Such as the A2A modes,A2G modes,and the history of development of them?Many thanks!
 
No A2G modes.

Sapfir-25 is a straightforward adaptation of Sapfir-23ML which has been discussed in some depth already.
 
Bump
Does anybody have more info on the avionics especially the FCS and the GCI?
http://www.ausairpower.net/TE-Foxbat-Foxhound-92.html

" The core of the weapon system was a massive 1,100 lb I-band air intercept radar, the Smerch A, designated by NATO as the Foxfire. Designed for high peak power output to burn through jamming by a target's defensive ECM, the Foxfire was a pulse Doppler design with a limited look-down capability, and has been described as comparable in this respect to the AWG-10 carried by later USN F-4s. It is not unreasonable to assume that AWG-10 components retrieved from wreckage in North Vietnam would have been closely examined by the designers of the Foxfire. Western sources credit the Foxfire with a Search/track range of 55/40 NM.
The Communists built the Foxfire with the objective of engaging targets at all altitudes, including the standoff missiles of the period which were larger and flew higher than the later ALCM/GLCM. The Foxfire unlike its Western contemporaries, was built entirely with vacuum tubes, a technology which the Communist block developed to a fine art at a time when Western designers opted for semiconductors. While bulky, maintenance intensive and power hungry, vacuum tubes were relatively insensitive to ambient temperatures and EMP and thus were well matched to the environmental extremes of Siberian winters and central Asian summers.
The Foxfire was tightly integrated with a RSIU-5 VHF datalink, NATO designation Markham, reportedly a solid state design, this datalink carried radar video from a ground based GCI scope to the cockpit CRT display of the Foxbat, and also carried radar video from the Foxfire to the GCI station. During an intercept, the Foxbat pilot could approach his target silently on GCI video, and then light up his radar once in position to launch and guide his missiles. The GCI operator could simultaneously advise the pilot while observing a repeated image of the Foxfire's video.
The Foxfire/Markham system was complemented with, by Communist standards, a comprehensive nav/comm fit, including the RSBN-2 short range nav, the SP-50 Swift Rod ILS and MRP-56P beacon receivers, an R-831 UHF comm, a RSB-70/RPS HF comm with an antenna embedded in the leading edge of the left tail, and an ARK-5 DF set. The customary SRO-2 Odd Rods IFF was complemented by a SOD-57M Air Traffic Control/Selective Identification transponder. A Sirena 3 crystal video radar warning receiver was also fitted, it is considered comparable to the Vietnam era APR-25."
 
Uragan-5B
Uragan-5B-80 RP-S /RP-28 Smerch [BIG NOSE]RP-SM Smerch-M
RP-25 / Smerch-A / Izdeliye 720 [FOX FIRE]

The MiG-25 used the RP-25 "Smerch-A" radar which has an interesting history. It goes back to 1954 and the Urugan-5 system, the first fully integrated and automated air defence system which was intended to counter new threats such as the B-58 Hustler. It combined multiple ground based radars and command datalinks with and an onboard radar able to detect bombers at least 25km away and capable of head-on engagements. NIIP's (Designer: F F Volkov) "Uragan-5B" radar was a major improvement on his earlier twin antenna Almaz design ("Uragan-1") and was intended to equip Mikoyan (I-75, Ye-150/152) and Sukhoi (T-37) heavy interceptors along with with K-6/K-7 (later, K-8/K-9-155/K-9-51) AAMs.

Uragan-5B was far in advance of contemporary Soviet radars, and implemented many advances in electronics and radar systems, including semi-conductors (116 vacuum tubes, 280 semi-conductor elements). It used a cassegrain antenna. It was designed as a monoblock, which slid into the nose of the aircraft and easily removed for maintenance. It was a real breakthrough in Soviet aircraft radar design. With smaller size and weight (220kg) than Almaz, it had greater jamming resistance and reliability, and detected bombers at 30km and reliably tracked them at 20km.

However slow progress with the heavy fighters, (both eventually cancelled), Uragan-5, and rapid advances in technology, meant new longer range missiles were now in development (K-80) which needed longer range radars.

NIIP by this time were redirected to SAM radar development so in 1958 Volkov was moved to OKB-339 (Phazotron) where he continued work on Uragan derivatives. Uragan-5B-80 was a major redesign for the K-80 missile, and added a new inverse cassegrain antenna with much improved characteristics (originally designed by NII-17). Detection range was increased to more than 50km and tracking range to 30-40km. This radar design was put into production for the Tu-128 as RP-S "Smerch" [BIG NOSE]

As soon as Smerch entered testing in the early 1960s Volkov embarked on another new version. RP-SA "Smerch-A" [FOX FIRE] increased detection range to 90-100km and tracking range to 50-70km. Initially intended for the Tu-128A which did not get built, it ended up equipping the MiG-25P interceptor and was retrofitted to the Tu-128 (as RP-SM) later on.

Smerch-A weighed about 500kg, was a low PRF pulse radar with inverse cassegrain antenna. It was the ultimate development of a family of radars started in 1954. A good comparison would be the F-4D's APQ-109 radar.

The Smerch-A1 as fitted to the MiG-25 prototypes introduced a second, secret operating wavelength of 2cm in addition to the standard 3cm to ensure the radar would function even in a heavy ECM environment. This was strictly prohibited from use in peacetime. By the time it entered production, improvements in jamming resistance and low-level clutter tolerance had been achieved. Smerch-A2 / Izdeliye 720M gave improved reliability, and was the standard production radar, and Smerch-A3 more improvements, which were fitted to later model MiG-25Ps as they rolled off the production line.

Around 1974 a developed "Smerch-A4" was proposed for the MiG-25-40M with lookdown-shootdown capability and R-40M missiles, but given that the MiG-31 prototype was close to first flight with the revolutionary Zaslon radar further MiG-25 developments were canned. Additionally the Sapfir-23 radar had a more promising method of clutter rejection.

N005 / Sapfir-25 / RP-25MN / S-500 [HIGH LARK]

Sapfir-25 was developed by a team under Kirpichev as a very high priority task after the defection of Viktor Belenko to Japan in 1976 compromised the MiG-25's radar making it highly vulnerable to western ECM. For speed of development, an existing radar had to be selected as the base, and the MiG-23ML's N003 radar, with its lookdown capability, was the obvious choice. Changes included the use of a larger antenna.

Detection range in lookup mode against a Tu-16 was 105-115km head-on. Tracking range against the same target was about 75-80km. Lookdown mode reduced these ranges to 27-30km and 22-25km respectively.

Detection range against a MiG-21 in lookup mode was 70km head-on, while tracking range was about 50-60km.

Weight was 337kg. It used an AVM-25 analog computer.

Compared to Smerch-A it could engage faster targets at higher altitudes, featured greater search and tracking range, provided lookdown/shootdown capability and close combat modes. It had 30° (±15deg) and 60° (±30 deg) azimuth search patterns, ±14° in elevation. It also had better anti-jamming protection. Azimuth scanning limits were slightly reduced to ±56° , elevation to +52/-42° , by the twist-cassegrain antenna design.
 

Attachments

  • Uragan-5B-1.jpg
    Uragan-5B-1.jpg
    64.8 KB · Views: 524
  • Uragan-5B-2.jpg
    Uragan-5B-2.jpg
    12.4 KB · Views: 509
  • Smerch-A.jpg
    Smerch-A.jpg
    68.2 KB · Views: 296

Attachments

  • RadarDisplay-3.jpg
    RadarDisplay-3.jpg
    29.9 KB · Views: 149
  • RadarDisplay-2.jpg
    RadarDisplay-2.jpg
    25.6 KB · Views: 143
  • RadarDisplay-1.jpg
    RadarDisplay-1.jpg
    30.1 KB · Views: 143
  • SmerchA-4.jpg
    SmerchA-4.jpg
    50.3 KB · Views: 131
  • SmerchA-3.jpg
    SmerchA-3.jpg
    50.6 KB · Views: 113
  • SmerchA-2.jpg
    SmerchA-2.jpg
    57.5 KB · Views: 218
  • SmerchA-1.jpg
    SmerchA-1.jpg
    40.3 KB · Views: 241
  • Sapfir25.jpg
    Sapfir25.jpg
    49.4 KB · Views: 167
Last edited:
Hello, i have some questions about MiG-25RB series.

1. What is under conical dielectric nosecone and what are under two tandem ventral dielectric panels of MiG-25RB? (under lateral dielectric panels is SRS-4 Romb-4)
2. exist any photos of MiG-25RBN (night FOTINT), MiG-25RR (RINT) and MiR-25MR (meteorological recon)?
3. It was build 27 MiGs-25R and 196 MiGs-25RB. How much from 196 is MiG-25RB, MiG-25RBS, MiG-25RBK, MiG-25RBV and MiG-25RBT?
 
Smerch-A3 more improvements, which were fitted to later model MiG-25Ps as they rolled off the production line.
Click to expand...
.

May i know these improvements were in what field?!. More improvements in resistance to jamming or i.e target identification?! or perhaps both?. ::)

Also, Are there any more details about the Smerch A-4 radar? I would be interested to know, how it actually differed from the Sapfir-25 radar and, are there any details about the Landysh' ECM system/set?!


Thank you,
 
RP-S Smerch
Detection range, Tu-16, 60% probability of detection : not less than 50km
Lock-on range, Tu-16, 90% probability: not less than 35-45km
Detection range: MiG-19, 30-45km
Lock-on range, MiG-19, 22-32km


Source: Tupolev Tu-128 "Fiddler" by Sergei Burdin, Nikolai Popov & Alan Dawes
 
I am closely reading the same book right now. I had no idea until seeing the photo posted above just how big the antenna was for the Smerch!

One question that I am unclear on (and at this point I am only halfway through the book): Was the Smerch-A retrofitted to modified Tu-128M aircraft in the late 1970s? The book seems to emphasize better cooling and upgraded missiles for low-altitude operation, but how did the upgraded Smerch unit itself differ? It's probably just something very obvious that I have missed, but figured that you are the guy to ask as I am genuinely curious.

On a side note, I am extremely impressed so far with the new Tu-128 book!
 
There is a short history of the Smerch-A series radars posted here earlier. A follow-up...

The wikipedia article on the R-40 missile claims that has a monopulse seeker. This apparently entered service on the MiG-25 in 1970. Given the state of Soviet electronics of the era, this seems somewhat questionable. I have done a bit of googling and found that most claims to this effect come from copies of the wiki article. The sole article that claims this and has its own origins is this one but I am not clear whether this is saying it was available on the first examples or some later model, the "R". The article is converted from Russian and is barely understandable in parts.

In any event, to guide an inverse monopulse missile you need a monopulse radar. Most descriptions of the Smerch-A claim it to be a pulse-Doppler unit with limited look-down. This generally implies klystrons or similar (phase changes will be a PITA in the seeker). The various images posted in the earlier thread show an interesting seeker head which appears to be a dielectric lens but I can't really say. I suppose it's also possible that there was a separate illumination system, but given the range of the R-40 and the lack of any visual indication of such, I don't believe this was the case.

The Smerch-A ultimately dates to the 1950s Urgan series, and I know that even 1970s Soviet radars still often used magnetrons, which would make all of this exceedingly difficult. Its entirely possible that these capabilities were added during one of the many upgrades to the Smerch, but details I find online are all confusing.

Can anyone add some clarity here?
 
Maury Markowitz said:
There is a short history of the Smerch-A series radars posted here earlier. A follow-up...

The wikipedia article on the R-40 missile claims that has a monopulse seeker. This apparently entered service on the MiG-25 in 1970. Given the state of Soviet electronics of the era, this seems somewhat questionable. I have done a bit of googling and found that most claims to this effect come from copies of the wiki article. The sole article that claims this and has its own origins is this one but I am not clear whether this is saying it was available on the first examples or some later model, the "R". The article is converted from Russian and is barely understandable in parts.
Click to expand...
True, R-40 uses a monopulse seeker. That time there was two approaches to semi active seekers. One uses continues wave illumination (or pseudo - continues). This allows in rather simply way to detect target, also on background of earth using Doppler processing. It also allows for conical scan method. It was used in Aim-7 up to version F.
The second method based on pulsed transmission. Its advantage - no need for the second, CW transmitter. But use conical scan is here is questionable due to lower "refresh rate" (PRF let say 1kHz) and the most importantly due to scintillation. So the better choice was to use monopulse seeker. And about the degree of complication, just two receivers instead of one... in big missile.... possible to do .. similar seeker was also in R-23 and so on
Use link http://airwar.ru/weapon/avv/k40.html with Google Translator - provided quite satisfactory results...
In any event, to guide an inverse monopulse missile you need a monopulse radar.
Click to expand...
No, why? On the other hand if you have technology to put monopulse seeker, you will be able to make monopulse radar... So monopulse radars were that time in Mig-21(S and later) -23 -25...

Most descriptions of the Smerch-A claim it to be a pulse-Doppler unit with limited look-down. This generally implies klystrons or similar (phase changes will be a PITA in the seeker). The various images posted in the earlier thread show an interesting seeker head which appears to be a dielectric lens but I can't really say. I suppose it's also possible that there was a separate illumination system, but given the range of the R-40 and the lack of any visual indication of such, I don't believe this was the case.

The Smerch-A ultimately dates to the 1950s Urgan series, and I know that even 1970s Soviet radars still often used magnetrons, which would make all of this exceedingly difficult. Its entirely possible that these capabilities were added during one of the many upgrades to the Smerch, but details I find online are all confusing.

Can anyone add some clarity here?
Click to expand...
It was in many threads on this forum. Look for more details and discussion what "is" Doppler radar and what is not to for example:
https://www.secretprojects.co.uk/threads/phazotron-sapfir-23-and-sapfir-25-radar.25/

in short: Mig-25 used two types of radar. The first one was Smierch-A(2). This one was purely pulse radar with no Doppler processing at all. But is was not limitation for high speed, altitude fighter. It was developed in 60tees and first used in Tu-128 interceptor. The next version was applied in Mig-25. That radar has some limited capability to detect targets on lower altitudes but rather based on space separation between target and background (in time and in direction) - so generally not much.
On the other hand, Mig-23 was intended to fight high altitude targets but also low altitude targets. So for them there was developed radar with Doppler processing, still based on magnetron, still LPRF. It was not so easy, the first production version has this mode not working , only version S-23DSz (or "III" cyrlic ) had somehow functioning Doppler mode (Mig-23M). But it has limited range, many sources says limited only rear hemisphere (actually I do not know why, maybe because very limited range, lower single scan probability of detect - due to many blind speeds). It had also continues wave illuminator (based on klystron) for R-23 missiles.
Then it was slightly improved in Mig-23ML (with switch Forward /Reverse hemisphere), with some extended range (due to improved sensitivity, power or similar). For low level targets claimed range was 15km (for Tu-16 size target)
Next radar on Mig-23MLA was (Amethyst N-003) - it was modernization of the previous with new element base, maybe even some digital signal processing elements. This improves range but especially for Doppler mode (up to 28 km for Tu-16 size target, about 20km for fighter size). There was also improved missiles R-24.

And, after Bielenko escape, Mig-25 electronics was compromised and there was decision to modernized Mig-25 electronics. As base they use radar from Mig-23 (Amethyst, N-003) so they create scaled up version (bigger array, maybe transmitters, not sure). As being bigger - it has somehow better detection ranges. New seeker for R-40 was based on seeker from R-24.

That's all.
 
Last edited:
And according to how use Doppler processing on magnetron based (non coherent), LPRF systems.. Well this was done in sixties, on ground radars, and was called Moving Target Indication. So idea is here (at least as I understand them) to memorize phase of transmitting pulse in some internal, coherent oscillator (hence called also COHO). So having memorized phase of the last pulse, while processing returns, you can take in account the phase of the last pulse and "correct returns " in receiver to obtain returns from consecutive pulses having the same, coherent phases. Regardless technical implementation, I like to think about this process like putting some phase shiftier in receiving path. The transmitted pulses are not coherent, but I know phase of each transmitted pulses in reference to some stable, coherent signal. So I can shift that phase in return signal to get all returns like in coherent radar. So that's why they were called "coherent on receive". In plane it was somehow more complicated - as radar moves.

(And in Mig-23 - instead of local COHO oscillator - there was used method with "external coherence" It use returns from ground (from sidelobes?) to make reference signal. Actually - this is not clear for me...)

This approach was tried on USAF Phantoms - but failed (USN Phantoms goes into direction of real pulse- Doppler radars, with HPRF, but over see it was easier to detect targets regardless hemisphere, than over land). It was practically implemented on Mig-23. Constructors were challenged by two problems: stability of components (you have to memorize signal in some delay lines between consecutive pulses, it is difficult doing this in analog way), and you have to have receiver with high dynamics to process weak echo of target on background of strong reflection from ground. In other hand - your receiver should not saturate, or decrease sensitivity while dealing with high amplitude signal (reflection from earth), as this will suppress also echo from target.
Later in Amethyst - they used new component base (including integrated circus and maybe some kind digital elements/processing), so this improve especially processing in Doppler mode, providing somehow tactically useful look down /shot -down radar. But still with many limitation comes from method* But this was in late 70 tees. And at that time in US they use or introduce fully coherent radars, working in HPRF, MED PRF and LPRF and so on).
 
*As example of limitation: you can set your "phase shiftier" in receiver to correct phase of the last emitted pulse. Thus this approach works for the recent pulse only. For example with PRF 1kHz - you receive returns unambiguously up to 150km., and up to that range - that method will work. But what about returns from above that range? They will have phases incorrectly changed (let say random phases), so they will be not coherent and Doppler processing for them will not work.
This seems to be not problem, but...

On the other hand in frequency area - the distance between blind speeds is equal to PRF. So in above example blind speeds (returns from ground) are separated about 1kHz. And as each blind zone is somehow wide (depending on radar bandwidth, and deflection of antenna from plane axis) actually - there is no space between them, to detect targets. So... lets... increase PRF.... For example to 4kHz... our unambiguous range drop to just 35km... and we can not see further (at least in Doppler processing)
Now in frequency domain there is some space between blind speeds... not much.. let say 2kHz... still there are returns from slow moving objects (like road traffic) and we can not recognize them... chance to detect target is limited to somehow 50%.. there is need to change PRF to overcome blind speeds... and we can not move antenna much to side as this increases blind speed zones .... So lets increase PRF to 8kHz... In frequency area - it starts to be quite comfortable, but our instrumental range just drop to 17km. And we can not detect targets further (at least in this Doppler mode) regardless its size (even B-52..)
8kHz - is PRF that start to be Medium PRF like. Having coherent transmitter, there is no need to "correct phase in receiver", and we can see further than the first unambiguous range. We are free to further increase PRF ... and set them according other design criteria (in range 8 - 16kHz or more). In system like above - it is not possible
 
@Maury Markowitz you seem to be suffering from some misconceptions about radar in general and Russian capabilities in particular

The wikipedia article on the R-40 missile claims that has a monopulse seeker. This apparently entered service on the MiG-25 in 1970. Given the state of Soviet electronics of the era, this seems somewhat questionable
Click to expand...

First monopulse radar was 1943. The british AI mk 23 radar on the Lightning used monopulse and was in service by 1960. French Cyrano I Bis radar used monopulse too in the same timeframe. Russia lagged a little in electronics, but this was 10 years old technology in 1970. AI Mk 23 used valves but was still monopulse.

Developed under the guidance of chief designer E.N. Genishta, the first domestic monopulse semi-active "radio" head PARG-12 used a number of new technical solutions. In particular, a two-mirror Cassegrain antenna was used to form a four-lobe directional pattern with an equal-signal deviation angle of up to 70. The GOS uses a calculator based on a sine-cosine rotating transformer, a range finder with two integrators, original circuits of a microwave generator and a receiving device with a logarithmic characteristic, which eliminates the danger of "blinding" at large drops in interference power.
Click to expand...

The R-40 seeker was created by the same OKB as the radar itself. Smerch-A used monopulse angle tracking.

In any event, to guide an inverse monopulse missile you need a monopulse radar. Most descriptions of the Smerch-A claim it to be a pulse-Doppler unit with limited look-down. This generally implies klystrons or similar
Click to expand...

Smerch-A is not and was never claimed to be pulse-doppler by anyone to my knowledge. Love to see a source for that. Its a pulse radar using a magnetron. It uses monopulse angle tracking, which is perfectly possible with a pulse radar and was a feature of most later pulse radars - it just needs a special design of antenna and some additional complexity in the receiver design. Smerch-A uses spatial target selection to detect targets below it, but the maximum range of this depends on the height of the MiG-25 and is useless at low level.

Monopulse is a signal processing technique. You could implement a monopulse AAM seeker that worked with a radar that didn't use monopulse angle tracking, but that would be a weird thing to design because then your radar's target tracking ability is worse than the AAMs, you lose your lock, and the missile loses its illumination.
 
Last edited:
From US exploitation reports of Belenko's MiG-25.

Airborne Intercent (A/I) Radar
The basic designator for the FOX FIRE A/I radar used on FOXBAT appears to be SMA. The radar processor and centralized fire control system is designated SMA 2. The circuitry of the radar processor and the fire control computer appears to be completely analog, using "peanut" vacuum tubes for IF/video with some semiconductor devices for power supply control and motor drive.

The A/I radar consists of an I-Band and a J-Band radar. The I-Band radar appears to serve as both a target tracker in range and angle as well as an illuminator for the semiactive missiles. A sample of the I-Band magnetron RF signal is sent by coaxial cable to each of the four missile pylons. A small horn is mounted on each pylon to provide this I-Band reference signal to each missile seeker head. Since there is no antenna scanning capability to allow the single J-Band feed to angle track, it appears that J-Band radar is range-only. No sample of the J-Band magnetron power goes to the pylons.

The radar antenna system contains a very complex feed system which is completely different from the simple feed assemblies seen on earlier Soviet A/I radars. The actual feed assembly is completely enclosed in a glass bell, suggestive of a pressurized system. The feed assembly contains at least four separate I-Band horns in the center with eight additional horns, probably J-Band, four on each side of the I-Band horns. These I-Band horns support the previous estimate of a LORO (Lobe On Range Only) track mode for the FOX FIRE radar. The function of these eight other horns is unknown. This new and sophisticated approach to antenna design is far advanced over known MIG-21 radar systems.

A thin layer of Radar Absorbent Material (RAM) is present on the bottom of the inner radome. The material is similar to that used on FIDDLER. It helps suppress ground clutter from side-lobe echoes. As yet there is no evidence of processing techniques which help to eliminate main beam clutter, i.e., to provide a look-down capability.

There is considerable emphasis on ECCM features, including:
  • Dual, separate I/J Band systems for range information
  • Dual channel I-Band angle tracking capability (specific configuration undetermined) believed capable of providing protection against amplitude modulated noise or deception angle scan rate ECM.
  • An additional antenna, basically an open-ended I-Band wave guide, believed to be a side-lobe blanker. It is located directly above the primary scanning antenna.
  • An additional I-Band feed system (function unknown) which consists of a two element dipole array located near the four horn I-Band tracking feeds.
  • Extremely high powered magnetrons. Some components (such as the isolator) consist of two identical devices in parallel for additional power handling capability. A rough estimate of power is 600 to 800 kW for I-Band and 300 to 400 kW for J-Band.
  • Countermeasures against rear-launched chaff exist and are believed to be similar to the MiG-21 SPIN SCAN radar, except a capability to handle both approaching and receeding targets has been added. The concept appears to be based on range rate determination to detect lock-on to stationary chaff.
  • Tunable transmitter magnetrons. There are four discrete preset I-Band frequencies which can be changed by simply changing a receiver preselection waveguide filter and changing switch settings on the radar central processor/ synchronizer. Measurements of this filter indicate the I Band frequency is 9327 MHz. The J-Band magnetron has two preset frequencies changed by turning a screw on the magnetron.
  • Dual-channel capability during tracking with the I-Band is probably accomplished by alternately lobing the four horns. This suggests that FOX FIRE has a scan-with-compression capability. The use of two RF bands would necessitate the jamming of both bands simultaneously. If only the I-Band channel were jammed, angle information would be provided by the I-Band while range information would be provided to the fire control computer by the J-Band, allowing for a missile launch.
  • Since the J-Band signal may have no scan capability, and no J-Band RF energy is fed to the missile seeker, the probable function of the J-Band signal is a range-only radar.
  • This raises the possibility that the pulsed J-Band portion of TWIN SCAN (carried on FLAGON E) is a range-only radar and not a missile illuminator as previously thought. Further analysis of the technology used by FOX FIRE is needed before any firm conclusions can be reached concerning the exact function of the J-Band signals.
Click to expand...

Source: https://www.secretprojects.co.uk/th...ding-mig-25-top-speed.4099/page-3#post-525663
 
Wow. 600-800 KW and 300-400 KW. I wonder what the duty cycle is. I assume for low PRF radar like that it will be about 1% or maybe even less i lean to the lesser one e.g 0.1%
 
overscan (PaulMM) said:
The A/I radar consists of an I-Band and a J-Band radar. The I-Band radar appears to serve as both a target tracker in range and angle as well as an illuminator for the semiactive missiles. A sample of the I-Band magnetron RF signal is sent by coaxial cable to each of the four missile pylons. A small horn is mounted on each pylon to provide this I-Band reference signal to each missile seeker head. Since there is no antenna scanning capability to allow the single J-Band feed to angle track, it appears that J-Band radar is range-only. No sample of the J-Band magnetron power goes to the pylons.
Click to expand...
Click to expand...
Many thanks for providing this Information.
A coaxial cable? Do we know the position of the horn or do we have any picture of this?
 
Missed this part:
The estimated power on the I-Band and J-Band radar magnetrons are three to four times that previously' estimated (200kw) for the FOX FIRE I-Band channel. The greater power could explain the long acquisition and extremely long missile launch ranges associated with the FOXBAT A.
Click to expand...
 
seems 0.01% duty cycle is reasonable, correspond to about 60 Watt of average power. This give calculated detection range of Smerch (SW-1,PD-50%, RCS target of 16 sqm) to 98 km, PD-90% or tracking is at 58 km.
 
The Wiki article on the R-40 missile claims it was the first inverse monopulse seeker to enter service, circa 1960. That's possible, but seems difficult for an aircraft and especially a missile seeker using tubes.

Looking at images of the Smerch-A posted here earlier, I don't see the multiple antennas one would normally associate with a monopulse system like you can clearly see in the AIRPASS. There's a sort of plastic cover (a polyrod?) that obscures things somewhat, but I can sort of make out what appears to be a single antenna within. In contrast, the similar gizmo on the Saphir seems to have a multi-way feed that suggests it was monopulse.

Someone has also posted an image of the R-40 seeker, and this appears to have only one waveguide from the antenna. This might just be the camera angle and cutaway, there could be another running the other direction, but in this case you would expect it to be at the top or bottom (doesn't have to be, but easier). Again, in contrast one can easily see the multiple antennas on, say, the R-27.

Anyone know for sure?
 
"Multiple antennas" is a feature of radars with simple parabolic antennas doing amplitude comparison monopulse where two or more overlapping radar beams are produced. We have descriptions of the PARG-12 seeker:

In the semi-active pulsed radar homing head PARG-12 of the R-40R missile, for the first time in domestic and world practice, a monopulse method of information processing and a range finder with two integrators were used, which ensured greater resistance of the seeker to the effects of amplitude interference compared to previously created heads with conical scanning. The GOS also embodied the original circuits of a stabilized microwave generator and a reference signal receiver. Unlike previously used circuits with automatic gain control, the logarithmic characteristic of the receiver implemented in this GOS eliminated “blinding” during sudden changes in interference power. The dissimilarity of the logarithmic receivers caused oscillations at the goniometer output with the so-called interperiod interference.

The PARG-12 head has a developed logic and high protection against interference combined with the target. A two-mirror Cassegrain antenna was used in the PARG-12 RGS to form a four-lobe directivity pattern necessary for organizing monopulse processing, as well as to ensure maximum (±70°) deviations of the equi-signal direction. The movable antenna mirror is irradiated by a stream that is stationary relative to the rocket. In this case, the equisignal direction of the radiation pattern is rotated by twice the angle of the mirror's lapel. On the basis of a sine-cosine rotating transformer, a calculator was created that converts the given overloads into a coupled coordinate system, taking into account the acceleration and deceleration of the rocket. This made it possible to build guidance according to the method of proportional navigation in the antenna coordinate system, when the projection of the full overload of the rocket on a plane perpendicular to the range line is proportional to the product of the estimated angular velocity of the range line and the approach velocity. Record bearings of the tracked target and guidance in the antenna coordinate system made it possible to intercept a high-speed target at large angles.
Click to expand...
Then also according to the exploitation report of Belenko's MiG-25, Smerch-A had a very complex feed with 4 I band feed horns:

The radar antenna system contains a very complex feed system which is completely different from the simple feed assemblies seen on earlier Soviet A/I radars. The actual feed assembly is completely enclosed in a glass bell, suggestive of a pressurized system. The feed assembly contains at least four separate I-Band horns in the center with eight additional horns, probably J-Band, four on each side of the I-Band horns.
Click to expand...
Therefore the antenna design is essentially similar to the Sapfir-23 or N019.

It is likely this was introduced in Smerch-A, and the Tu-128 RP-S Smerch and the R-80 missiles were not monopulse.
 
Last edited:
 
overscan (PaulMM) said:
Uragan-5B
Uragan-5B-80 RP-S /RP-28 Smerch [BIG NOSE]RP-SM Smerch-M
RP-25 / Smerch-A / Izdeliye 720 [FOX FIRE]

The MiG-25 used the RP-25 "Smerch-A" radar which has an interesting history. It goes back to 1954 and the Urugan-5 system, the first fully integrated and automated air defence system which was intended to counter new threats such as the B-58 Hustler. It combined multiple ground based radars and command datalinks with and an onboard radar able to detect bombers at least 25km away and capable of head-on engagements. NIIP's (Designer: F F Volkov) "Uragan-5B" radar was a major improvement on his earlier twin antenna Almaz design ("Uragan-1") and was intended to equip Mikoyan (I-75, Ye-150/152) and Sukhoi (T-37) heavy interceptors along with with K-6/K-7 (later, K-8/K-9-155/K-9-51) AAMs.

Uragan-5B was far in advance of contemporary Soviet radars, and implemented many advances in electronics and radar systems, including semi-conductors (116 vacuum tubes, 280 semi-conductor elements). It used a cassegrain antenna. It was designed as a monoblock, which slid into the nose of the aircraft and easily removed for maintenance. It was a real breakthrough in Soviet aircraft radar design. With smaller size and weight (220kg) than Almaz, it had greater jamming resistance and reliability, and detected bombers at 30km and reliably tracked them at 20km.

However slow progress with the heavy fighters, (both eventually cancelled), Uragan-5, and rapid advances in technology, meant new longer range missiles were now in development (K-80) which needed longer range radars.

NIIP by this time were redirected to SAM radar development so in 1958 Volkov was moved to OKB-339 (Phazotron) where he continued work on Uragan derivatives. Uragan-5B-80 was a major redesign for the K-80 missile, and added a new inverse cassegrain antenna with much improved characteristics (originally designed by NII-17). Detection range was increased to more than 50km and tracking range to 30-40km. This radar design was put into production for the Tu-128 as RP-S "Smerch" [BIG NOSE]

As soon as Smerch entered testing in the early 1960s Volkov embarked on another new version. RP-SA "Smerch-A" [FOX FIRE] increased detection range to 90-100km and tracking range to 50-70km. Initially intended for the Tu-128A which did not get built, it ended up equipping the MiG-25P interceptor and was retrofitted to the Tu-128 (as RP-SM) later on.

Smerch-A weighed about 500kg, was a low PRF pulse radar with inverse cassegrain antenna. It was the ultimate development of a family of radars started in 1954. A good comparison would be the F-4D's APQ-109 radar.

The Smerch-A1 as fitted to the MiG-25 prototypes introduced a second, secret operating wavelength of 2cm in addition to the standard 3cm to ensure the radar would function even in a heavy ECM environment. This was strictly prohibited from use in peacetime. By the time it entered production, improvements in jamming resistance and low-level clutter tolerance had been achieved. Smerch-A2 / Izdeliye 720M gave improved reliability, and was the standard production radar, and Smerch-A3 more improvements, which were fitted to later model MiG-25Ps as they rolled off the production line.

Around 1974 a developed "Smerch-A4" was proposed for the MiG-25-40M with lookdown-shootdown capability and R-40M missiles, but given that the MiG-31 prototype was close to first flight with the revolutionary Zaslon radar further MiG-25 developments were canned. Additionally the Sapfir-23 radar had a more promising method of clutter rejection.

N005 / Sapfir-25 / RP-25MN / S-500 [HIGH LARK]

Sapfir-25 was developed by a team under Kirpichev as a very high priority task after the defection of Viktor Belenko to Japan in 1976 compromised the MiG-25's radar making it highly vulnerable to western ECM. For speed of development, an existing radar had to be selected as the base, and the MiG-23ML's N003 radar, with its lookdown capability, was the obvious choice. Changes included the use of a larger antenna.

Detection range in lookup mode against a Tu-16 was 105-115km head-on. Tracking range against the same target was about 75-80km. Lookdown mode reduced these ranges to 27-30km and 22-25km respectively.

Detection range against a MiG-21 in lookup mode was 70km head-on, while tracking range was about 50-60km.

Weight was 337kg. It used an AVM-25 analog computer.

Compared to Smerch-A it could engage faster targets at higher altitudes, featured greater search and tracking range, provided lookdown/shootdown capability and close combat modes. It had 30° (±15deg) and 60° (±30 deg) azimuth search patterns, ±14° in elevation. It also had better anti-jamming protection. Azimuth scanning limits were slightly reduced to ±56° , elevation to +52/-42° , by the twist-cassegrain antenna design.
Click to expand...
An excellent article on Uragan. Can you give me your references please as I am writing a book on Soviet air defence c 1963-1972?
 

Авторизация - АО "НИИП имени В.В. Тихомирова"

www.niip.ru www.niip.ru
In the mid-1950s, V.V. Tikhomirov managed to achieve a special resolution of the USSR Council of Ministers on the microminiaturization of electrical radio elements to create a new generation of radars. In 1958, the new Almaz-3 radar, weighing only 160 kg, successfully passed state tests and was recommended for adoption as part of the T-3 fighter-interceptor. The Almaz-3 radar had two antennas isolated from each other - a survey and an aiming one, which was natural for the "locators", but significantly complicated the life of the "aircraft".

For the first time in our country, the task of combining survey and aiming antennas was implemented on the Uragan-5B radar, which is part of the Uragan-5 interception complex. The Uragan-5B radar, designed for the E-150 interceptor, was a single monoblock container weighing 220 kg. In its design, 116 electron tubes and 280 semiconductor elements were used. In terms of its characteristics, the radar was not inferior to the best foreign analogues, having a detection range of more than 30 km from a bomber and provided stable tracking from a range of 20 km, which made it possible to use both cannon and missile weapons. Unfortunately, work on the Uragan-5B radar was stopped in the early 60s due to a change in the ideology of building air defense systems. The backlog was later used to create a radar for the MiG-25P interceptor.

Thanks to the efforts of Viktor Vasilievich and his closest associates Grishin V.K., Rastov A.A., Matyashev V.V., Sapsovich B.I. -shnyh" systems. Its distinguishing feature is a tough focus on the final result, the desire for unconditional and complete satisfaction of customer requirements. At the same time, each new development was based on advanced, non-traditional solutions, many of which were ahead of the best world achievements.
Click to expand...

See also https://www.secretprojects.co.uk/threads/early-soviet-ai-radar.18019/

Sources were:

Books in English e.g. Yefim Gordon's Red Star series ( MiG-25, Soviet Heavy Interceptors, Sukhoi Interceptors, Lavochkin's Last Jets) , the Tu-128 book by Burdin, OKB MiG, etc
Books in Russian e.g. a Russian book on the History of Radar in the USSR, MiG: Flying Through Time
Russian books on Tu-128, MiG-25 etc
Magazine articles in English (articles in Air Fleet etc)
Magazine articles in Russian (https://www.niip.ru/info/articles/ has a decent selection like this one on V.V. Tikhomirov)


One pro tip is to search in Russian e.g. search for

РЛС "Ураган-5Б"

And you should get a lot of interesting leads.

You can use airwar.ru as a way of finding the Russian text to search for e.g. look for relevant aircraft articles and copy paste the text.
 
Last edited:
THE 'HURRICANE' THAT GENERATED THE 'WHIRLWIND'
Part II

By Andrei Fomin

Due to the complex nature of the task assigned and delays with developing
R15-300 engines and Uragan-5 (Hurricane-5) system's elements, the
resolutions of the Council of Ministers of 16 April and 4 June, 1958
reshaped the objectives and terms of building the interceptors. This time,
the following aircraft were to be submitted for testing: two E-150
R15-300-powered aircraft armed with K-8 missiles; two E-152A
R11F-300-powered aircraft armed with K-9 missiles; single E-152
R15-300-powered aircraft armed with K-9 missiles. Besides, the K-9 AAM-armed
E-152A and E-152 aircraft were to be fitted with the K-9 system with TsP-1
radar, developed by the Design Bureau-1 (now the Almaz central design
bureau) and featuring 30-km detection range, instead of the Uragan-5
intercept system's airborne component fitted with the Uragan-5B radar. The
prototypes equipped with R11F-300 engines were to begin their trials in the
third quarter of 1959. Trials of the aircraft powered by R15-300 were
postponed until the second quarter of 1960. Nonetheless, the commencement of
comprehensive testing of the on-board elements of the Uragan-5 intercept
system together with K-8 missiles in the fourth quarter of 1958 was done
owing to the I-75 and I-75F aircraft.

While the Uragan-5 system components were being tested on the I-75 and
I-75F, late November 1958 witnessed the assembly of the first E-150
prototype fitted with R15-300 engines. For the first time, the designers use
the honeycomb filler that ensured the 10%-18% reduction of weight of
ailerons, flaps and empennage while enhancing their stiffness. During the
first six months of 1959, the aircraft was undergoing ground testing
programme as well as all-mode engine testing. However, due to repeated
delays in deliveries of the Uragan-5 system components, the work on that
prototype were cancelled. Later, the E-150 was used for the flight testing
and research of the R15-300 engine capable of higher altitudes. This also
cause the cancellation of the work on the I-75 and I-75F. The whole second
E-150 prototype's technological backlog was later used to build the E-152.
The maiden flight of the R15M-300-powered E-150 was made by test-pilot A.V.
Fedotov only on 8 July, 1960. However, after the fifth sortie, the trials
were suspended due to destruction of the engine accessory gear box. On 18
January, 1961, the permission was granted for flying with a new engine
delivered on 3 December, 1960. In 1961, the flight trials resulted in 36
sorties made, speed of 2,890 km/h (M=2.65) at 20,000 m developed and static
ceiling of 23,250 m reached.

The authorisation to use R11F-300 engines until R15-300s are delivered
ensured the kick-off of the E-152A flight trials. The OKB-155 design bureau
was quick to design and submit production draft documents (June-October
1958). The E-152A interceptor was assembled in June 1959 and handed over to
undergo the factory test programme (the second E-152A prototype has been
under production until October 1959. However, later on, it was converted
into the second E-152 prototype powered by R15-300 engines). The aircraft
also featured honeycomb fillers. The first flight made by the E-152A took
place on 10 June. The prototype was piloted by G.K. Mosolov. Yu.N. Korolyov
was appointed the leading engineer. During the first six months of 1959, the
aircraft's stability and controllability were tested. The trials produced a
speed of 2,135 km/h (M=1.99) at an altitude of 13,700 m, as well as a static
ceiling of 20,600 m. Due to the abrupt deterioration of the directional
stability, further acceleration was not pursued. The K-9 weapons suite (as
part of the Uragan-5 intercept system) development was not performed due to
the delays in deliveries of some TsP-1 radar units as well as the SAZO-SPK
command-link and transponder system.

In early 1958, the OKB-134 of the State Committee on Aviation Systems (early
in 1958, the Ministry of Aviation Industry was reorganised into the State
Committee on Aviation systems - GKAT), headed by Chief Designer Ivan
Toropov, was tasked with designing the K-9 missile for E-152A and E-152
interceptors. The work was being done in cooperation with the KB-1 design
bureau of the State Committee on Radioelectronics, which was responsible for
the guidance system development. In line with the schedule, the experimental
units were expected to be submitted for the joint official testing in the
second quarter of 1960. However, in 1959, the development of the K-9
missiles was handed over to the OKB-155 design bureau. There the missile was
redesignated as K-9-155, with a design team having been set (head - V.G.
Korenkov).

The K-9-155 missile was developed as part of the K-9 weapons system. It was
intended to be an all-aspect missile capable of hitting targets from any
direction, including on the head-on and collision courses. Based on the
missile's estimated minimal kinetic load (especially close to the target
while attacking it from any aspect), it was decided to base the missile
guidance on the parallel convergence homing method. Such a method ensured
minimal angular velocity of the missile/target line. The X-shape all-moving
wing aerodynamic configuration was selected. The longitudinal control was
exercised through the all-moving wings. The roll control was exercised
through four ailerons mounted on the fixed stabiliser. The stabiliser was
fitted with four rollerons to enhance roll damping. The missile comprised
the TsR-1 semi-active radar pulse homer, APTs-18 autopilot, TsRV-1 pulse
radiofuse, HE warhead, I-60 safety/trigger device and PRD-56 single-chamber
two-mode powder motor.

For flight trials the following variants of the K-9 missile were made -
combat version (item 90); ballistic version (item 91) - to evaluate the
missile's aerodynamic and ballistic performances when flying with fixed
wings, as well to evaluate its aircraft separation safety and its engine
performances; software testing version (item 92) - to evaluate the missile's
software-controlled aerodynamic and ballistic performances and to check the
operation of the autopilot, power supply unit and pneumatic system in
flight; telemetric version (item 93) - to evaluate the operation of the
homer- and fuse-equipped missile as part of a closed system
(aircraft-missile-target) without detonating the warhead when travelling
close to the target.

In mid-1959, the OKB-155 design bureau developed and submitted for
experimental production the drafts of two K-9 variants - the ballistic and
software-controlled ones with the drafts of the rest versions having been
developed by late 1959. The plans made provision for manufacturing 32
experimental missiles in al variants (item 91 - 20 units, item 92 - 5, item
93 - 5 and item 90 - 2). By late 1959, first 6 units of item 91 had been
made, and the manufacturing of item 92 began. Before late 1960, 21 item 91s,
7 item 92s and 4 item 93s had been completed. The production of combat
versions was postponed due to problems with development and deliveries of
BR-6A telemetric stations (developer - Plant #567), UTR-13-2 signal
conditioning units, reworked APTs-18 autopilots, power supply units and òçó
(the KB-1 was responsible for everything). In 1961, 26 missiles were made
(item 90 - 3, item 91 - 6, item 92 - 11, item 93 - 6). Early in the same
year, three launches of the K-9 (item 91) missile were performed. The
launcher was mounted on the ground-based stand which simulated an aircraft
underwing launching pylon.

Since the deliveries of the Uragan-5 system's elements have been repeatedly
disrupted, in 1960 the OKB-155 design bureau took up designing the E-152-9
intercept complex intended to operate as part of the Dal automatic guidance
system. The E-152-9 system comprised an interceptor aircraft; the k-9 weapon
system comprising the TsP-1 radar and K-9 missiles with guidance equipment;
the VB-158 computer; Meteorit SAZO-SPK command-link and transponder system
(to operate as part of the Vozdukh-1 semi-automatic guidance system; in 1961
the intercept system was completely converted to operate as part of the
Vozdukh-1 semi-automatic guidance system and was redesignated as E-152-9-V);
AP-39 autopilot; KSI compass system; flight navigation aids' set (NP-1 and
PP-1), as well as a range of other systems. By the end of the year, the
automatic aircraft control and guidance system had been completed, control
circuits had been tested at the dynamic instrument test stand in conjunction
with real avionics and systems in all intercept modes the E-152A and E-152
interceptors were capable of - programmed climb, ground-controlled guidance
to the target in azimuth and altitude, homing, recovery from attack and
levelling under semi-automatic and fully automatic control. The bench tests
confirmed that the equipment provides the pilot with effective and safe
control of the aircraft in all flight modes. To ensure control circuit
dynamic stability and sighting accuracy, the TsP-1 radar elements were
reworked, as were the VB-158 computer and PP-1 flight director indicator.
Upon completion of the flight trials in August 1960, the E-152A was fitted
with the E-152-9 intercept system's components. Late in 1960, flight testing
of individual elements (TsP-1 radar, AP-39 autopilot, VB-158 computer and
flight director devices) began. Soon, the aircraft furnished with the K-9
launchers was redeployed to the Air Force Research Institute's proving
ground to carry on with trials. There, it made 39 sorties. During flight
tests in 1961, the E-152A aircraft launched 10 K-9 missiles (5 item 91s, 5
item 92s). The trials confirmed that the missile's aerodynamic and ballistic
performances had matched the estimate ones. The missile underwent wind
tunnel tests at the TsAGI, its warhead underwent ground test at the GSKB-47
proving ground of the State Committee on Defence Materiel (GKOT). The
missile systems were also subjected to preproduction and bench testing,
mathematical modelling and physical simulation in all modes, as well as a
range of other tests. Based on the warhead's ground tests and radiofuse's
flight trials, the GKAT's NII-2 research institute (currently GosNIIAS
research institute) calculated combat missile efficiency rate which
confirmed that the required performances were achieved.

Simultaneously with the E-152A development, designing and working draft
issuance on the E-150 conversion into the E-152 began in 1958. To mount
avionics and K-9 missiles on the E-152 aircraft required that appropriate
changes to the E-150 design should be made. Due to the TsP-1 radar
installation, the fuselage's fore section was stretched in length and had
its diameter enlarged too. A all-welded pressurised bay was made to house
the radar components. The bay had cooling and compressed air pressurisation
systems. The cockpit was a little bit elevated to give the pilot a better
view. The right wing housed a compartment for the frequency-matching unit of
the TsP-1 radar. The wing was also redesigned to carry K-9 missiles instead
of K-8s. As the fore section of the fuselage weight increased, a new
nosegear strut for the KT-93 660x160 mm wheel (instead of the 600x155 mm
KT-78) had to be designed. To enhance flight safety, the NP-27 emergency
pump with hydraulic accumulators had to be installed into the booster
hydraulic system. The pump was to ensure the landing with the killed engine.
Besides, the stabiliser control, previously exercised by the APS-4MK
electric device, was cancelled.

The first E-152/1 aircraft was manufactured in 1960, and its ground testing
began. On 16 March, 1961, the aircraft was sent for factory tests after it
had been fitted with the R15-300 engines. Its first flight took place on 21
April. The aircraft was piloted by test-pilot Georgy Mosolov. For the
factory tests, test-pilot Alexander Fedotov and project engineer M.P.
Proshin were appointed. Before mounting the TsP-1 radar, there was a 263-kg
counterload in the fore fuselage section. During the factory tests, which
were conducted from 16 March, 1961 till 8 January, 1962 and from 20 March
till 11 September, 1962, 67 sorties were carried out, including five ones
with K-6 missile mockups.
In that period, three world records were set by the E-152/1 aircraft which
was officially redesignated as E-166:
- on 7 October, 1961, test-pilot A.V. Fedotov set a world speed record along
a 100-km closed track. An average speed of 2,401 km/h was developed,
sometimes reaching 2,730 km/h.
- on 7 July, 1962, test pilot G.K. Mosolov set a world speed record. On the
15-25 km speed test course, an average speed of 2,681 km/h was reached in
both directions. During one of the approaches, the aircraft developed a
speed of over 3,000 km/h.
- on 11 September, 1962, test-pilot P.M. Ostapenko set a world altitude
record on a 15-25 km course, which equaled 22,670 metres with a speed of
2,500 km/h.

Meantime, the manufacture of the second E-152/2 flight prototype was
completed, and on 8 August, 1961 it was sent to the airfield for flight
trials. The suction system of the boundary layer from the air intake spike
was improved through increasing the guard net's open flow area. To enhance
longitudinal stability, the fuel consumption sequence was changed. After the
ground tests had been over, the E-152/2's maiden flight took place on 21
September, 1961. The factory tests had continued until 3 July, 1962 (test
pilots Pyotr Ostapenko (leader), Aleksandr Fedotov, project engineer A.N.
Soshin) and were cancelled following the 16th sortie due to the programme
termination, as the KB-1 design bureau was re-oriented for other tasks and
it had to stop producing autopilots, homers, power units and other finished
elements of the K-9 weapon system. Furthermore, the Air Defense development
concept was changed, with air defence missile systems having been given the
highest priority. At the same time, however, the work on the new intercept
system - S-155 - began.

In line with the directive of the Council of Ministers dated 5 February,
1962, a provision was made both to further develop the E-155
R15B-300-powered aircraft in the reconnaissance aircraft and interceptor
variants and to convert two E-152s for testing elements of the S-155
intercept system being under development. In accordance with that, it was
envisaged to fit the E-152/1 with new R15B-300 engines and carry out its
flight trials. Besides, a decision was taken to equip the E-152/2 with the
Smerch-A radiocontrol and homing system, as well as with K-80 missiles in
order to test and prepare them for the E-155P interceptor.

In 1962, a working draft was developed with all necessary drawings issued.
The work on conversion of the E-152/1 into the E-152M/1 began after the
world records had been set on it. The R15B-300 engines, featuring enhanced
thrust and an all-mode nozzles, were installed on the aircraft. Extra fuel
load was added. It was housed by three detachable grotto tanks and by the
first fuselage tank. It was envisaged to install foreplanes. Due to this,
the E-152/1 fuselage's fore and rear sections were redesigned. The work had
been finished by the end of 1962, but sub-standard engines had to be
mounted. The completion of the second prototype was also delayed due to the
lack of the engines. It was assembled only in the first half of 1963,
equipped with sub-standard engines, too, and was sent to the factory flight
testing on 14 June, 1963. The E-152M/2 aircraft was equipped with R15B-300
engines and two K-80 all-aspect homing missiles, mounted on the wing tips.
The aircraft was equipped with the Smerch-A radar with the radio
interception system, SAU-1I Polyot automatic control system with flight
navigation devices, Lazur-M command link system, RSBN-2 Iskra short-range
navigation and landing system and the KSI compass system.
The R15B-300 engine ?8, delivered in November 1963 and installed on the
E-152M/1, ensured only the ground test programme, with the engine started.
The flight trials were not carried out due to the ban on operating the
engine in the air. In 1963-1964, the flight tests failed to begin because
there were no R15B-300 flight-ready engines on hand. That is why further
work on them was cancelled, and it was the E-152A aircraft that was used for
experiments.

In 1962-1965, the E-152A interceptor was used in flight tests of the BPNV-1
programmed climb computer as well as of the SAU-1I damper prototype.
However, on 29 January, 1965, the E-152A crashed during the tests, killing
test pilot Igor Kravtsov in the process. By then, the first prototypes of
the E-155R reconnaissance aircraft and E-155P interceptor had been
undergoing flight testing.

In conclusion, it is necessary to note that the aircraft with the factory
designation E-155 was, at first, slated for operating as part of the
Uragan-5 intercept system. In accordance with the above resolution of the
Council of Ministers of 4 June, 1958, three E-155 interceptors powered by a
combined powerplant (turbojet engine + liquid-propellant rocket engine) were
to be submitted for factory flight trials in the second quarter of the 1960.
They were designed to intercept targets at an altitude of up to 30-35 km at
a 140-170 km range. Their maximum speed was to be 3,500-4,000 km/h. At the
first stage of the testing, the armament was to consist of K-9 missiles, and
further K-155 missiles. Besides, development of four unmanned reusable STOL
interceptors, designed to operate from unpaved airstrips, was planned and
produce them for tests in the fourth quarter of 1961. However, it did not
proceed beyond the conceptual design stage. Despite the fact that the
Uragan-5 and E-152-9 (E-152-9V) intercept systems were not destined to pull
the alert duty, the wealth of experience, gained from their designing,
contributed considerably to the success of further development programme.
Click to expand...
 
oborona.ru

К 100-летию со дня рождения Б.И. Сапсовича

Основополагающие идеи руководителя антенного отдела позволили НИИП им. В.В. Тихомирова стать лидером в создании РЛС с электронным сканированием
oborona.ru oborona.ru

TsKB-17 became the place where the famous scientific schools of the 20th century were born.

The work of B.I. Sapsovich in the creative, young team of TsKB-17 had a huge impact on his formation as a scientist and practitioner. Heated discussions of theoretical and practical issues of creating modern technology (and the discussions sometimes lasted until late at night), interaction with prominent scientists - all this for Boris Iosifovich became a solid base, the foundation of his future independent projects.

By 1954, the load on the staff of NII-17 and personally on V.V. Tikhomirov, accustomed to bearing personal responsibility for each of the areas of work, has grown so much that he is becoming stronger in the idea of the need to form a separate enterprise with an aviation-radar line of work. Initially, on March 1, 1955, a branch of the Moscow NII-17 was formed based on the territory of the LII named after M.M. Gromov, which a year later was transformed into an independent enterprise - Special Design Bureau No. 15 (OKB-15) of the Ministry of Radio Industry. Together with V.V. Tikhomirov transferred 379 specialists from NII-17 to the branch, who laid the foundation for a new workforce. Among them was B.I. Sapsovich, who in 1957 became the head of the antenna department.

The practical participation of Boris Iosifovich in the development and introduction into serial production of radar sights for the most mass-produced MiG-15 fighter, while still within the walls of NII-17, allowed him to gain experience not only in design, but also in organizing activities in creating modern aircraft weapon control systems. B.I. Sapsovich also contributed to the first success of OKB-15 - the completion of development and adoption in November 1955 of the Izumrud-2 radar as part of the first domestic K-5 air-to-air guided missile system on the MiG-17 fighter . When developing typical radar units to improve their reliability and simplify operation, B.I. Sapsovich led the work on the creation of antenna-waveguide systems.

The first completely independent topic of the OKB 15 team was the development of the Uragan-5B locator based on a new element base. When it was created, the most advanced achievements of radar and radio electronics at that time were implemented. And the antenna-waveguide units, designed with the direct participation of B.I. Sapsovich, and then embodied in metal, showed in the process of testing that a young, but already experienced team led by Boris Iosifovich is ready to conquer new heights. And such an opportunity presented itself very soon.

At the turn of the 1960s. work on the Uragan-5B interception system for the E-150 high-altitude interceptor was canceled. The ideology of building an air defense system has changed, but the aircraft could not yet comply with it, in particular, it was still impossible to realize a long flight in supersonic. The scientific and technical groundwork for this program was subsequently used to create the MiG-25P interceptor.
Click to expand...
 

Similar threads

Back
Top Bottom