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Iranian Space program

Sineva

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This photo highlights the problem with ISA SLV program.

Simorgh size “class” SLVs should be putting 700-1250kg payloads into LEO if you look at competitors in same size class, but Simorgh is only doing 150KG.

Even much smaller SLV are doing 3-4x Simorgh.

Points to weak/outdated engines or fuel mixture or both.
Thats because at the time,back in the early-mid 2000s,iran had no choice but to use/repurpose whatever existing tech it had access to,ie late 40s rocket engine tech,which used less efficient fuels,for the first stage and mid 60s engine tech for the second stage,except that the engines used for the 2nd stage were originally small vernier engines that had to be both modified and then pushed far beyond their original limits,naturally this meant reliability suffered badly.
My own hope is that iran has acquired the paktusan/rd-250 engine from the dprk,as this would give iran the potential to build boosters with the ability to put multi-ton payloads in leo.
 

TheImmortal

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Thats because at the time,back in the early-mid 2000s,iran had no choice but to use/repurpose whatever existing tech it had access to,ie late 40s rocket engine tech,which used less efficient fuels,for the first stage and mid 60s engine tech for the second stage,except that the engines used for the 2nd stage were originally small vernier engines that had to be both modified and then pushed far beyond their original limits,naturally this meant reliability suffered badly.
My own hope is that iran has acquired the paktusan/rd-250 engine from the dprk,as this would give iran the potential to build boosters with the ability to put multi-ton payloads in leo.

Well it’s 2022 and Iran is still not using powerful enough engines.

North Korea just annnounced they will sending multiple payloads into space in the future. If North Korea ends up having a more successful space program than Iran, it will be a national embarrassment considering Iran’s technical/scientific resources and monetary resources vs the hermit kingdom.
 

drmeson

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Few photos I have for the project we talked about. more will come later..cheers.

I have included some of the various Satellites built and an engine to propel them to the orbit in here. The Cube Sat shown is part of 60 sat project for commercial purposes
cube sat.png


sat1.jpg


sat2.png


sat3.png


sat4.jpg


sat eng.png

Parse sat
View attachment 822458
View attachment 822461
View attachment 822460

Amazing work @aryobarzan

SAFIR 1A/1B/KAVOSHGAR
Ist Stage: 1 x modified Shahab-3 Engine producing KN 365 with Liquid N2O4 /UDMH
2nd Stage: 2 × R-27 Zyb Engine producing 37 KN with Liquid N2O4 /UDMH
Max payload to LEO: 50 KG

(5 Successful Launches since 2009)

Flight No.
Date & Time (UTC)
Payload
Type
Outcome
Remarks
1​
2 February 2009​
Omid
Safir-1​
Success​
First successful orbital launch of Safir making Iran the ninth country to develop an indigenous satellite launch capability
2​
15 June 2011​
Safir-1A​
Success​
Rasad-1 was launched on the maiden flight of the Safir-1A​
3​
3 February 2012​
Safir-1B​
Success​
New configuration of the Safir carrier rocket, featuring a larger second stage with 20% more thrust.​
4​
2 February 2015​
Fajr
Safir-1B​
Success​
First Iranian satellite with orbital maneuverability using cold-gas thrusters.​


ZOLJANAH
1st Stage: 1 x Solid Fueled engine producing 725 KN
2nd Stage: 1 x Solid Fueled engine producing 725 KN
3rd Stage: 2 × R-27 Zyb Engine producing 37 KN with Liquid N2O4 /UDMH
Max payload to LEO: 220 Kg

(1 Successful sub-orbital launch)

Flight No.
Date & Time (UTC)
Payload
Outcome
Remarks
1​
31 January 2021​
Success​
first Sub-orbital test flight​


SIMORGH

1st Stage: 4 × modified Shahab-3 engines + 4 Vernier’s Producing 1590 KN with Liquid fuel N2O4 /UDMH
2nd Stage: 4 × R-27 Zyb Vernier engines producing 50 KN Liquid with Liquid fuel N2O4 /UDMH
3rd Stage: 1 x Saman-1 producing 15 KN with Solid Fuel
Max payload to LEO: 350 Kg

(1 Successful launch)

Flight No.
Date & Time (UTC)
Payload
Type
Outcome
Remarks
1​
19 April 2016​
No Payload​
Simorgh​
Success​
Sub-orbital test flight​


QASSED
1st Stage: 1 Ghadr-H engine producing 50 KN with Liquid fuel N2O4 /UDMH
2nd Stage: 1 x Salman Engine producing 50 KN with Solid Fuel
3rd Stage: 1 x Saman-1 producing 15 KN with Solid Fuel
Max payload to LEO: 50 Kg

(2 Successful launches)

Flight No.
Date & Time (UTC)
Payload
Type
Outcome
Remarks
1​
22 April 2020, 04:00​
Noor 1​
Success​
444 x 426 km orbit, 59.8 degree inclination​
2​
8 March 2022, 05:06​
Noor 2​
Success​
495 x 513 km orbit, 58.3 degree inclination​


---------------

My next post will be about Engines.
 

OldTwilight

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This photo highlights the problem with ISA SLV program.

Simorgh size “class” SLVs should be putting 700-1250kg payloads into LEO if you look at competitors in same size class, but Simorgh is only doing 150KG.

Even much smaller SLV are doing 3-4x Simorgh.

Points to weak/outdated engines or fuel mixture or both.
simorgh is white elephant
 

TheImmortal

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So the satellite itself has propulsion. that make it interesting...

I was under the impression the tip propulsion is part of the 3rd stage not the satellite itself. It merely puts the satellite in super accurate orbit and then detaches.

This appears to be a cube sat based on IMA Media video, so it will need to “open up” thus it cannot be attached to the tip axis.

So where do you see the satellite itself has propulsion?
 

mohsen

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This photo highlights the problem with ISA SLV program.

Simorgh size “class” SLVs should be putting 700-1250kg payloads into LEO if you look at competitors in same size class, but Simorgh is only doing 150KG.

Even much smaller SLV are doing 3-4x Simorgh.

Points to weak/outdated engines or fuel mixture or both.
Maybe you should compare it with South Korean bigger rocket Naro-1, it's RD151 engine, and 100kg payload!
 

Dexon

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I was under the impression the tip propulsion is part of the 3rd stage not the satellite itself. It merely puts the satellite in super accurate orbit and then detaches.

This appears to be a cube sat based on IMA Media video, so it will need to “open up” thus it cannot be attached to the tip axis.

So where do you see the satellite itself has propulsion?

my bad. i thought salman is last stage and that could be part of satellite
 

TheImmortal

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Maybe you should compare it with South Korean bigger rocket Naro-1, it's RD151 engine, and 100kg payload!

Naro-1 is a 2 stage rocket while Simorgh is 3. Naro is a retired design after just a few launches. So you failed to make a point.

Maybe Simorgh like Naro belongs to the retired recycle bin if it cannot have a successful launch this year.
 

mohsen

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Naro-1 is a 2 stage rocket while Simorgh is 3. Naro is a retired design after just a few launches. So you failed to make a point.

Maybe Simorgh like Naro belongs to the retired recycle bin if it cannot have a successful launch this year.
Point was payload on an up to date engine. having a third stage wouldn't have jump from 100kg to 1500kg.

Simorgh is planed to be retired whether it achieves a successful launch or not. Zoljanah will take the role.
 
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TheImmortal

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Point was payload on an up to date engine. having a third stage wouldn't have jump from 100kg to 1500kg.

Simorgh is planed to be retired whether it achieves a successful launch or not. Zoljanah will take the role.

Yeah it was a failed and useless design hence why it never made it past 3 launches. Point of 2 vs 3 stage was that SK was technically more powerful for doing its work with 2 stages instead of 3! Less stages = more advancement if all things are equal.

If you notice both SK and IRI rockets were developed around same time. Ancient tech at this point.

So explain why Zoljanah uses a liquid 3rd stage instead of Simorgh solid 3rd stage and make Zoljanah all solid?

Another head scratching decision by ISA
 

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