ISRO General News and Updates

Okabe Rintarou

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Bro thank you for posting these slides, always find them informative.
Just a bit of confusion regarding the upper stage and the second stage of the future variants of the gslv.

This is what i knew or we knew in general that future variants of gslv will have a second stage powered by sce-200 engine with 120t fuel mass/thrust in total and also coupled with the 32t variant of the current upper stage using the same engine ce-20.



But now in this particular slide, we get a 160t 2nd stage with 27t upper stage, ummm why?

I don't exactly recall but i think either you or someone else posted here another ppt where it showed that we will have mk4 and mk5 variants of the gslv, basically a casual upgrade of second stage, third stage and maybe boosters i am not sure. So are these suggesting that configs may change or just old?
Most likely its old config. New config is centered around SC-120 and C-32 stages, which are already being manufactured as we speak (propellant tanks already built). The entire idea is to be modular at least in stage construction to lower costs and achieve economies of scale. Would be counterproductive to go a SC-160 stage now.

One additional query, are we going to use se-200 engine in any boosters of gslv?
Not in GSLV, and likely not in HLV either. But in SHLV.
SCE-200 based stages like SC-120 will be used as boosters in SHLV and another stage SC-400 being used as boosters in another, heavier config of SHLV.
 

Karthi

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Bro thank you for posting these slides, always find them informative.
Just a bit of confusion regarding the upper stage and the second stage of the future variants of the gslv.

This is what i knew or we knew in general that future variants of gslv will have a second stage powered by sce-200 engine with 120t fuel mass/thrust in total and also coupled with the 32t variant of the current upper stage using the same engine ce-20.



But now in this particular slide, we get a 160t 2nd stage with 27t upper stage, ummm why?

I don't exactly recall but i think either you or someone else posted here another ppt where it showed that we will have mk4 and mk5 variants of the gslv, basically a casual upgrade of second stage, third stage and maybe boosters i am not sure. So are these suggesting that configs may change or just old?




One additional query, are we going to use se-200 engine in any boosters of gslv?

Can't give a straight forward answer bro it depends upon ISRO , they are developing tech and they can use it for anything they like . That's a good thing . There may be because of the slides preparation , they just showing the plans not the real specs .

SCE 200 may use GSLV as a testbed before it is used in ULV and RLV . So it is possible to integrate with GSLV missions everything depends upon the requirements .
 

FalconSlayers

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ISRO is developing Entry Descent and Landing (EDL) technologies for its Mars Orbiter Mission-2. Request to refer the slide for the technologies under development. Aeroshell, IAD and supersonic retro propulsion are most suitable technologies for mars landing.
1636454834287.jpeg

 

Cheran

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View attachment 117939


PS4 stage for debris removal with robotic arm , very good for removing chinese junks from Space using low cost PS4 spend rocket . Indian satellites can refuel using refuelling probe

View attachment 117940View attachment 117942View attachment 117943View attachment 117944View attachment 117945

An indian juggad , a swarm of drones to recover spend rocket engines and reusing. a cluster of drones with wit a net recovered a RH 200 booster .

View attachment 117946View attachment 117947View attachment 117948
1636463979170.png


Hope we make progress on the debris capturing satellite with arms.

CCP has recently launched one, Shijian 21 that has a robotic arm.



 

Vamsi

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1st unmanned mission before Aug 2022, and 2nd unmanned mission & manned mission in 2023
My guess , if we assume 9 months gap between each mission then G1 in July /Aug 2022, G2 in April/ May 2023 & finally manned mission G3 in Feb / March 2024, right before election 😂😂 and it will be fun to watch momo begum & liberandus crying while the manned Gaganyaan takesoff 😜😂
 

sorcerer

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Isro enters X-band telemetry & command regime with new 18m antenna | India News - Times of India

Compared to S band, which operates with 2GHz to 4GHz, X band functions in 8GHz to 10GHz. Sources at Isro, terming this a major milestone, said this has two advantages: "First, it increases the speed of commands and second, reduces possibility of any interference given that the S band is now also used by telecom companies for 5G."
 

Varoon2

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Nice^, is it Indian made? Awaiting some good news about impending launches from ISRO!

I just read the article, great, it is indigenous. But check out the sick, single comment at the end of the article.
 

sorcerer

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isro: Space diplomacy: Isro preparing to launch nano satellite for Bhutan | India News - Times of India


Bengaluru: As part of New Delhi’s space diplomacy, the Indian Space Research Organisation (Isro) is preparing to launch a nano satellite built by engineers from the neighbouring country with the help of Indian scientists in the second PSLV mission that’s in the pipeline.
As reported by TOI earlier, Isro has in its pipeline three Earth Observations Satellites (EOSs): Two of them — EOS-4 (Risat-1A) and EOS-6 (Oceansat-3) — will be launched using Isro’s workhorse PSLV and the third one, EOS-2 (Microsat), will be launched in the first developmental flight of the Small Satellite Launch Vehicle (SSLV).

 

Karthi

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Karthi

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Plasma Source For The Ground Testing of Satellite Solar Panels. Developed a ground test facility for LEO and GEO like space environments. To study the detrimental effects of arcing on the satellite solar panels, IPR has successfully developed an indigenous Spacecraft Plasma Interaction eXperiment (SPIX) facility at FCIPT.


The SPIX facility with ECR plasma source..jpg

The SPIX facility with ECR plasma source

Image of satellite solar panel damaged due to arcing .jpg

Image of satellite solar panel damaged due to arcing.


In order to reduce satellite weight, it is desirable to furnish power at higher voltages and lower currents. The high voltage satellite power systems suffer the drawback of arcing on the satellite solar panel surface. In some cases, such arcing can cause complete disruptions of satellite power system. This is a serious financial and strategical loss to the space industry.


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Low Energy Ion Beam Facility.jpg

Low Energy Ion Beam Facility.


Hall Effect Plasma Thrusters (HEPT) are under investigation as a technology aiming to achieve thrust with high exhaust velocities in satellites. In HEPT plasma forms in a narrow annular channel and interact with inner ceramic wall. Ejected ions can erode the ceramic at the ejection point edge. The eroded material may eventually deposit on the crucial parts of the satellite and degrade their efficiency most prone in this case are solar cells. Erosion can also expose the underlying magnetic yoke, causing the magnetic field profile to be altered and change HEPT functionality. Therefore, the investigation of thruster anode liner erosion and choice of material is very important for its long and stable operation. PSED/IPR group has recently completed a MoU with Vikram Sarabhai Space Centre (VSSC)/ISRO, Thiruvananthapuram. Under this MoU, a Low Energy Ion Beam facility was developed at FCIPT/IPR to investigate the erosion properties of the ceramic material developed by VSSC/ ISRO to be used as Anode Liner Material in HEPT. in-situ experiments were performed to investigate the material erosion behavior at various energies, fluence at elevated temperature under this project. With joint efforts of IPR and VSSC, this material has been approved to be used in the indigenously developed HEPT for Indian Satellites. This project was carried out by a team consisting of Akshay Vaid, Basanta Parida, Vivek Pachichigar, Sooraj K. P. and Mukesh Ranjan.
 

not so dravidian

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View attachment 119397
Low Energy Ion Beam Facility.


Hall Effect Plasma Thrusters (HEPT) are under investigation as a technology aiming to achieve thrust with high exhaust velocities in satellites. In HEPT plasma forms in a narrow annular channel and interact with inner ceramic wall. Ejected ions can erode the ceramic at the ejection point edge. The eroded material may eventually deposit on the crucial parts of the satellite and degrade their efficiency most prone in this case are solar cells. Erosion can also expose the underlying magnetic yoke, causing the magnetic field profile to be altered and change HEPT functionality. Therefore, the investigation of thruster anode liner erosion and choice of material is very important for its long and stable operation. PSED/IPR group has recently completed a MoU with Vikram Sarabhai Space Centre (VSSC)/ISRO, Thiruvananthapuram. Under this MoU, a Low Energy Ion Beam facility was developed at FCIPT/IPR to investigate the erosion properties of the ceramic material developed by VSSC/ ISRO to be used as Anode Liner Material in HEPT. in-situ experiments were performed to investigate the material erosion behavior at various energies, fluence at elevated temperature under this project. With joint efforts of IPR and VSSC, this material has been approved to be used in the indigenously developed HEPT for Indian Satellites. This project was carried out by a team consisting of Akshay Vaid, Basanta Parida, Vivek Pachichigar, Sooraj K. P. and Mukesh Ranjan.
Interesting. Hall effect plasma thrusters were successful tested by Bellatrix aerospace.

I wonder whether they wud have taken such detailed and microscope study.

Maybe because they only paln to use it for 500kg and below satellite??

https://www.google.com/amp/s/swaraj...ts-indias-first-privately-built-hall-thruster
 

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