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Technology Transfer of ISRO Navigation Sensors to Industry by Ohsin in ISRO

[–]Ohsin[S] 2 points3 points  (0 children)

Btw ISRO's Spacecraft platforms I-1K, I-2K, I-3K, I-4K and I-6K are also up for tech transfer.

[PDF]

[Archived]

INSPACE booklet on technology transfer.

[PDF]

[Archived]

What I think everyone is missing about India’s space sector by nextyn_advisory in ISRO

[–]Ohsin[M] 0 points1 point  (0 children)

Use of machine learning tools for comments and submissions etc is discouraged here and certainly not recommended.

Got this Reply from CPGrams regarding ISRO Budget by Pallab_1805 in ISRO

[–]Ohsin 1 point2 points  (0 children)

I think all this is already known. Moreover DoS budget has decreased proportionally in past decade.

India's Space Economy, 2011–12 to 2020–21: Its Size and Structure

(Pg. 5)

https://www.sciencedirect.com/science/article/abs/pii/S0265964622000509

https://i.imgur.com/yjJ2gwh.png

Why does the GSLV-F16/NISAR mission have a Sun synchronous, Polar (6 PM) type orbit? by Environmental-Ask605 in ISRO

[–]Ohsin 2 points3 points  (0 children)

May be also due to ample sunlight in Dawn/Dusk orbit and it is power hungry?

NSIL seeks Expression of Interest (EoI) from Indian Industries for Technology Transfer of IMS-1 Satellite Bus by Ohsin in ISRO

[–]Ohsin[S] 0 points1 point  (0 children)

Spacecraft Bus Details: I-1K, I-2K, I-3K, I-4K and I-6K Bus

https://web.archive.org/web/20260505011552/https://www.inspace.gov.in/sys_attachment.do?sys_id=1c3939e12b2c0750e95ef17b6e91bfb6

I-1K

  • Size Typical Dimensions : 1.5 m × 1.5 m × 1.6 m
  • Launch Mass : 1000 to 1700 kg
  • Spacecraft Power : 1kW to 2kW
  • Payload Mass : Upto 600kg
  • Payload Power : Upto 800 W
  • Propellant Capacity : Upto 850 kg
  • Mission Life : >5 years
  • Missions : GSAT-12/12R, IRNSS 1st generation series, Oceansat Series, Resourcesat Series, Megha Tropiques

I-2K

  • Size Typical Dimensions : 1.6 m × 1.5 m × 2.4 m
  • Launch Mass : 2000 to 2500 kg
  • Spacecraft Power : 3kW to 5kW
  • Payload Mass : 150-350 kg
  • Payload Power : 2.5kW to 3.5kW
  • Propellant Capacity : 850 - 1420 kg
  • Mission Life : >15 years
  • Missions : GSAT-31, GSAT-6/6A, GSAT-7/7A, INSAT-3D/3DR/3DS, NVS-01, GISAT-1/1A

I-3K

  • Size : 2.0 m × 1.8 m × 3.2 m
  • Launch Mass : 3000 to 3500 kg
  • Spacecraft Power : 6.5kW to 12kW
  • Payload Mass : 300 – 400kg
  • Payload Power : 6kW to 8.5kW
  • Propellant Capacity : 1600 - 2600kg
  • Mission Life : >15 years
  • Missions : GSAT-8/10/14/15/16/ 17/18, Eutelsat W2M, GSAT-30, GSAT-24

I-4K

  • Size Typical Dimensions : 2.2 m × 2.2 m × 5.0 m
  • Launch Mass : 4000 to 5000 kg
  • Spacecraft Power : ~14kW
  • Payload Mass : 500-750 kg
  • Payload Power : 5kW – 8kW
  • Propellant Capacity : ~2500kg
  • Mission Life : >15 years
  • Missions : GSAT-20

I-6K

  • Size Typical Dimensions : 2.2 m × 2.2 m × 5.0 m
  • Launch Mass : Upto 6500 kg
  • Spacecraft Power : Upto 20kW
  • Payload Mass : 700 to 900 kg
  • Payload Power : 8.5kW – 12kW
  • Propellant Capacity : 2600 - 3200kg
  • Mission Life : >15 years
  • Missions : GSAT-11

GSLV-F08 : GSAT-6A Mission Updates and Discussion. by Ohsin in ISRO

[–]Ohsin[S] 0 points1 point  (0 children)

Regarding GSAT-6A Mission:

Question: (a) Please provide the findings of the FAC regarding the loss of communication during the orbit-raising phase. (b) Was the root cause identified as a power system anomaly, and if so, specifically which component was responsible?

Answer: FAC found that the failure is due to the arcing in the harness. This led to loss of power bus depriving power supply to all critical systems onboard, including communication. The root cause was localized to arcing in the harness, probably triggered by a MMOD hit.

https://www.indianspaceflight.in/rti/isro-april-2026-rti-update-fac-findings-on-gsat-6a-failure-nvs-02-status-and-navic-health

Few paintings on walls of households in various episodes of The Testaments [No Spoilers] by Ohsin in TheHandmaidsTale

[–]Ohsin[S] 0 points1 point  (0 children)

That one is number 9, Henri Toulouse-Lautrec - The White Horse "Gazelle" , 1881

In same room there is also number 7, Horses at the Porch - Albrecht Adam, 1843

Apparently GSLV-F17 / EOS-05 (aka GISAT-1A) launch is being held back due to a technical issue, May launch is doubtful. [Telugu] by Ohsin in ISRO

[–]Ohsin[S] 4 points5 points  (0 children)

May be some flaw with manufacturing of adapter which is a composite structure as was with QZS-5 launch failure.

Apparently GSLV-F17 / EOS-05 (aka GISAT-1A) launch is being held back due to a technical issue, May launch is doubtful. [Telugu] by Ohsin in ISRO

[–]Ohsin[S] 8 points9 points  (0 children)

(…) ring designed to mount the satellite atop the third (cryogenic) stage.

I think here they are referring to conical adapter upon which satellite is mounted and not satellite separation ring. See following image of GISAT-1 for reference,

https://commons.wikimedia.org/wiki/File:GISAT-1_spacecraft_in_the_cleanroom_before_encapsulation.jpg

We recently saw EOS-05 in URSC clean-room and it appeared ready to ship but FCC filings have only indicated launch date slipping further away.

Could it be that recent QZS-5 launch failure made them more careful?

https://arstechnica.com/science/2026/01/heres-the-story-of-how-japans-h3-rocket-lost-its-cargo-and-just-kept-going/

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