India's Moon Exploration Program

[Vamsi]

Indeed, this is what landing of Perseverance rover mission 2 years back was.

Notice that velocity at seperation of ,"sky crane+preserverance rover" from the parachute was just 83m/s when compared to 1600m/s velocity for CY-3 lander during initiation of deboost burn....so Mars lander will be small.... @Indx TechStyle

 

[Vamsi]

Is Chandrayaan-4 and LUPEX same? Typing Chandrayaan-4 on Google returns LUPEX in result.

Yes same

 

[Indx TechStyle]

Notice that velocity at seperation of ,"sky crane+preserverance rover" from the parachute was just 83m/s when compared to 1600m/s velocity for CY-3 lander during initiation of deboost burn....so Mars lander will be small.... @Indx TechStyle

Small or bigger?
It would need bigger retro thrusters in this case.

 

[FalconSlayers]

Yes same

So I don't think CY-4/LUPEX would be a big burden on ISRO, since we're supposed to just build the lander, Japanese are gonna do the rest. They just want to have their rover at any cost on the moon's South Pole.

 

[Tactical Doge]

Is Chandrayaan-4 and LUPEX same? Typing Chandrayaan-4 on Google returns LUPEX in result.

Yeah
Japs should have their own naming system for it

So we can call it Kaguya-2/chandrayaan-4, or something like that

 

[TopWatcher]

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Inka alag hi kuch chal rha h

Yeh ISRO se bhi bade scientist hai.

 

[Tactical Doge]

Yeah
Japs should have their own naming system for it

So we can call it Kaguya-2/chandrayaan-4, or something like that

Unpopular opinion


Somnath in his Gareeb scientist interview said he's open to taking naming suggestions from youngsters

Ditch the Chandrayaan tag, it literally just means moon vehicle
LUPEX can be named Tsukiyomi-Soma
Both are lunar deities of the respective countries


Chinese did the same with Chang'e

 

[Vamsi]

Small or bigger?
It would need bigger retro thrusters in this case.

I'm talking about entire weight of the lander, let us assume if we decided to use every subsystem of CY-3 lander for a Mars lander by making necessary modifications, then the lander will weigh very less, because of less delta-V budget (90m/s instead of 1600m/s) around 600 kg instead of 1750 kg because of less fuel requirement, same 800N thrusters can be used

 

[omaebakabaka]

Landed bit at slope. Is it lander inclined or rover angle ?

This is actually better from comms pov, but wonder if rover left NE or NW on the downhill side? Looks like NE?

 

[Vamsi]

I'm talking about entire weight of the lander, let us assume if we decided to use every subsystem of CY-3 lander for a Mars lander by making necessary modifications, then the lander will weigh very less, because of less delta-V budget (90m/s instead of 1600m/s) around 600 kg instead of 1750 kg because of less fuel requirement, same 800N thrusters can be used

Just did some rough calculations, 300 kg rover can be landed using a 500kg lander, & 800kg entry capsule, weighing a total of 1600 kg , this can be launched by a 2200kg data relay orbiter, which can easily be launched by a LVM-3

 

[omaebakabaka]

Just did some rough calculations, 300 kg rover can be landed using a 500kg lander, & 800kg entry capsule, weighing a total of 1600 kg , this can be launched by a 2200kg data relay orbiter, which can easily be launched by a LVM-3

Ratio of 0.6? What is the entry capsule, the one from which lander seperates?

 

[TopWatcher]

Ratio of 0.6? What is the entry capsule, the one from which lander seperates?

Yes, to save it from entry burn.

 

[Vamsi]

Ratio of 0.6? What is the entry capsule, the one from which lander seperates?

Yep this thing

 

[omaebakabaka]

Yep this thing
View attachment 220467

Does it act as relay for sometime or its crashed already or deorbited/deorbits at some point? Sorry I have not had time to keep up...

 

[Rassil Krishnan]

Yep this thing
View attachment 220467

Why didn't they just commit a conventional landing with a parachute and thrusters and try a sky crane maneuver. What is the advantage of it.

 

[Physx32]

No, Mars lander will likely be handled by NGLV. LVM3 won't handle any light or heavy Mars lander.

Given Mars has atmosphere, has huge weight, most part of weight will be absorbed in heat shields and putting large thrusters leaving little space for any meaningful scientific payload for a 5 tonnes class probe.

So no, LVM3 is unlikely to handle Mars landing (or lander payload will be incredibly small even if they manage somehow). Still, very unlikely.

ISRO has a good opportunity to send an orbiter mission to one of the ice giants. No one has done such a thing till now and very little is known about the planets. ISRO and Indian universities will have a huge advantage to study these planets and publish papers before the western universities.

Regarding Mars, our existing LVM3 can easily send a rover like Spirit/Opportunity to Mars. Spirit was launched by Delta-II heavy which has lower payload capacity than LVM3.

 

[DumbPilot]

Govt needs to increase ISRO budget. A Saturn V class rocket is needed for a serious and meaningful future space endeavour.

Not very sustainable if we expend that short term. The SLS program is a good look as to how our own HLV program should proceed, but currently we don't require that payload capacity. First step should be to nail the human spaceflight and orbital rendezvous before attempting something more ambitious with humans.

 

[Vamsi]

Does it act as relay for sometime or its crashed already or deorbited/deorbits at some point? Sorry I have not had time to keep up...

It enters Mars Atmosphere, it deploys parachute, then the lower heat shield will be separated,after that the back shell will be separated, then lander lands using onboard thrusters

 

[Vamsi]

ISRO has a good opportunity to send an orbiter mission to one of the ice giants. No one has done such a thing till now and very little is known about the planets. ISRO and Indian universities will have a huge advantage to study these planets and publish papers before the western universities.

Regarding Mars, our existing LVM3 can easily send a rover like Spirit/Opportunity to Mars. Spirit was launched by Delta-II heavy which has lower payload capacity than LVM3.

The problem is not about rover, but about orbiter, if we include orbiter total payload will weight between 3000-3500kg....& Orbiter is must for this mission, for data relay as well as to create DEMs for lander

 

[Vamsi]

Why didn't they just commit a conventional landing with a parachute and thrusters and try a sky crane maneuver. What is the advantage of it.

Can you rephrase your question, I didn't get it