ISRO Plans Reusable Launch Vehicle (RLV-TD) Test Flight in 2013

[Srinivas]

This is also the Dream of Abdul Kalam

 

[The A-5]

How much payload can it carry?

Once this method of space exploration gets operational, the cost of sending satellites to orbit will be a lot less
than what it is now. Lots of money can be saved.

 

[trident2010]

Good development. Still need to master many crucial technologies including cryogenic engine one. Due to its limited budget ISRO don't conduct experimental launches frequently and therefore wait little bit longer to perfect it.

 

[arp2041]

How much payload can it carry?

Once this method of space exploration gets operational, the cost of sending satellites to orbit will be a lot less
than what it is now. Lots of money can be saved.

Some Specifications about RLV (TSTO) [should not be confused with a AVATAR SSTO]:

10 Ton to LEO and GTO payload capability.

Vertical take off.

Semi-cryogenic booster stage with avg. Isp of 330 seconds and cryogenic orbiter stage with avg. Isp of 400 seconds.

Total lift off weight < 700 tons.

Winged body booster that will boost the orbiter to Mach 10 at an altitude of 80-100 km then separate and return to launch site and land conventionally on an air-strip.

Orbiter will deploy the payloads in the intended orbits and then deboost, re-enter and land on airbags or vertically on legs.

Vehicle structure designed for 100 flights and engines for 50 flights.

Turn around time should be 30 days.

Payload fraction = 2%.

Cost effectiveness < 1000 US $/ kg for LEO payload.

Antariksh: ISRO Reusable Launch Vehicle Program: AVATAR & TSTO

 

[S-DUCT]

Some Specifications about RLV (TSTO) [should not be confused with a AVATAR SSTO]:

10 Ton to LEO and GTO payload capability.

Vertical take off.

Semi-cryogenic booster stage with avg. Isp of 330 seconds and cryogenic orbiter stage with avg. Isp of 400 seconds.

Total lift off weight < 700 tons.

Winged body booster that will boost the orbiter to Mach 10 at an altitude of 80-100 km then separate and return to launch site and land conventionally on an air-strip.

Orbiter will deploy the payloads in the intended orbits and then deboost, re-enter and land on airbags or vertically on legs.

Vehicle structure designed for 100 flights and engines for 50 flights.

Turn around time should be 30 days.

Payload fraction = 2%.

Cost effectiveness < 1000 US $/ kg for LEO payload.

Antariksh: ISRO Reusable Launch Vehicle Program: AVATAR & TSTO

Payload to GTO and LEO are quite good.
Why don't ISRO scraps GSLV mk3/4 And concentrate on This project.

 

[arp2041]

Payload to GTO and LEO are quite good.
Why don't ISRO scraps GSLV mk3/4 And concentrate on This project.

It will be just the kind of BLUNDER which we did in the case of LCA, where we din't ever built a 3rd gen ac (even 2nd gen Marut was designed by a German) indigenously & were going for a 4th gen ac, now the same 4th gen ac is delayed since we now need a 4.5 gen ac with changing times.

Every Tech. leaps requires going step by step, ISRO had always a plan for PSLV in the 1980s but it din't stop testing/launching ASLV/SLV at that time, PSLV has become a workhorse of ISRO now only b'coz of the experience gained by the launch of ASLV/SLV.

It's good that ISRO will have many options in the near future as a launch vehicle & will not just depend on the PSLV anymore. PSLV, GSLV mk2/3, RLV, AVATAR, etc.

It will analyze as to which launcher makes sense for the launch & is a cost effective solution based on the payload & other considerations.

Simply put, for reaching third floor of a house, one doesn't skip first two floors

 

[Screambowl]

If you are alluding to the RLV-TD design then thats not the RL vehicle. RLV-TD is a low cost concept that aims to demonstrate technologies required for the first stage of the RLV. The solid booster has nothing to do with the RLV, but to achieve a particular mission profile for second stage of the RLV-TD that looks like shuttle. The shuttle on top of the solid booster is actually a scaled down version of the first stage of the RLV and will be used to establish corresponding technologies. Second stage of the RLV will be derived from technologies established through Space capsule recovery experiments.

The RLV

The Technologies

Thing is, the RLV TD is supported on Truss bars which joint the solid booster to the orbiter. The point is it might come out as a weak point during launch due to vibration created by big symmetric object at the top comparative to the booster.

 

[Screambowl]

ISRO is working on the Two-Stage To Orbit (TSTO) vehicle design instead of earlier planned Single Stage To Orbit (SSTO), i just see the launcher & the booster as the Scaled-up version of the earlier SRE experiment conducted by the ISRO, as than, PSLV acted as a sort of booster while SRE was designed to be a smaller version of a Re-entry Vehicle, i see no problems whatsoever in this one, since if ISRO can get a success with smaller design, so can it get the same with a much larger one.

I want to know will the booster have smaller cross section area than the orbiter?

 

[manofwar]

GSLV Mk.III, IRNSS-1, Mangalyaan and now TSTO............It's going to be a hell of an year for ISRO!!!

 

[jarves]

EXCELLENT THREAD!!!
Thanks to @arp2041

 

[Brahmos_2]

what is the status of this project.?

 

[jarves]

what is the status of this project.?

I think its currently on track.

 

[IND151]

https://www.google.co.in/url?sa=t&r...AoN4Tm-r_Dxi5_UGovRf1OQ&bvm=bv.61965928,d.bmk