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Indian Space Capabilities

ISRO is saying ULV won't be ready before 2020, assuming semi-cryogenic engine testing goes according to plan.

So HLV won't be ready until 2030 by earliest then. Still, good to play ahead. Plus, ISRO is one of the few government organizations that has shown it can deliver what it promises if given time and budget.
 
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@gslv mk3 I didn't got one thing. Improved variant of GSLV Mk3 will have capacity of 6 tonnes GTO and 15 tonnes to LEO.
And that is same as that of maximum capacity of ULV.
So, why need ULV? Is this not the rebuilding same rocket? o_O
 
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eppa ??

The information about stages and engines are new,I suppose

No CE-60 :cry:



That's wrong

1. A 200 tonne propellant loading LOX and kerosene booster stage powered by a 2,000 kN thrust semi-cryogenic engine operating on stage combustion cycle.

2. A 50 tonne LOX-LH2 propellant loading cryogenic stage powered by twin CE 20 cryogenic engines.

3. A 10 tonne LOX-LH2 propellant loading cryogenic stage powered by a CE 20 cryogenic engine.

Source: Indian Space Capabilities | Page 279

The information I posted is taken directly from VSSC .
 
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The information I posted is taken directly from VSSC .

So we have another HLV ?

And that is same as that of maximum capacity of ULV.
So, why need ULV? Is this not the rebuilding same rocket?

I guess they are going for a modular approach,replacing the booster stages to achieve different payloads and for different mission profiles.
 
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So we have another HLV ?


I guess they are going for a modular approach,replacing the booster stages to achieve different payloads and for different mission profiles.

Yup .... looks like they are studying two different concepts of HLV with 10 tons to GTO payload capacity .
 
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Yup .... looks like they are studying two different concepts of HLV with 10 tons to GTO payload capacity .

I think this one is better...since it relies on existing/under development engines and not on CE 60,which is still at conceptual design stage

ith kandaayirunnallo alle ?

Russian tie-up to boost ISRO’s semicryogenic launcher plan - The Hindu

ISRO is working on its new-generation, Rs. 1,800-crore third rocket programme, called the semi-cryogenic launch vehicle, to beef up its current portfolio of the PSLV and the GSLV. It will use space-grade kerosene and liquid oxygen as fuel and is meant to pitch spacecraft totally weighing six to ten tonnes to heights of 36,000 km. This would be double the lifting power of the GSLV and triple that of the PSLV. Only the U.S. and Russia have this technology.
 
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I think this one is better...since it relies on existing/under development engines and not on CE 60,which is still at conceptual design stage

ith kandaayirunnallo alle ?

Russian tie-up to boost ISRO’s semicryogenic launcher plan - The Hindu

ISRO is working on its new-generation, Rs. 1,800-crore third rocket programme, called the semi-cryogenic launch vehicle, to beef up its current portfolio of the PSLV and the GSLV. It will use space-grade kerosene and liquid oxygen as fuel and is meant to pitch spacecraft totally weighing six to ten tonnes to heights of 36,000 km. This would be double the lifting power of the GSLV and triple that of the PSLV. Only the U.S. and Russia have this technology.

It's about the developement of Indian Semi-cryos ...... Russia providing a test facility to test our semi-cryos untill our facility comes online .

But the weight I think is wrong ..... most probably 6 to 10 tons to GTO ..... nobody launches directly to GEO .
 
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It's about the developement of Indian Semi-cryos ..

No bro,look at this

ISRO is working on its new-generation, Rs. 1,800-crore third rocket programme, called the semi-cryogenic launch vehicle, to beef up its current portfolio of the PSLV and the GSLV. It will use space-grade kerosene and liquid oxygen as fuel and is meant to pitch spacecraft totally weighing six to ten tonnes to heights of 36,000 km.
 
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Actually, even after a 100 tonnes capacity SHLV, we will see a bigger rocket because they may need to transfer 50 tonnes to TLI to land humans there. So, these projects may be platform for that.
 
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What is full form of LVM3 ?

LVM3 - ISRO

At 4.0 tons to GTO, it would be able to power nearly any heavy satellite into order giving India almost full independence from foreign launch vehicles.

Afterwards, the LVM3 will be modified again by replaced the L110 Core Stage with a Semi-Cryogenic stage SC-160, and then use a more modular initial booster stage to cost-effectively launch different payloads in the 1.5, 3.0, 4.5, and 6.0 tons to GTO. This would give India complete independence in launching even the heaviest commercial 5 ton satellites to GTO and it would also ISRO to use a single, Unified Launch Vehicle (Hence the name ULV) to replace both the LMV3 and the PSLV rockets reducing costs, logistics, and manufacturing by only using 1 vehicle.

Afterwards the engines of the ULV can be uprated and their fuel size increased, while the solid rocket boosts could be replaced with cryogenic or semi-cryogenic stages to increase payloads for far off missions like Lunar landings. As you can see in the previous page there are a number of different concepts that are ongoing and being studied.

For launch vehicles that require re-usability instead of expendibility, ISRO has an entirely different plan by making a space plane called AVATAR, which will be undergoing test missions on a scaled vehicle called RLV-TD (Reusable Launch Vehicle Technical Demonstrator).
 
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At 4.0 tons to GTO, it would be…………………………………………
LVM3 has a capacity of 6 tonnes to GTO and 15 tonnes to LEO. The rocket test fired last year was a test rocket so was underpowered. LVM3 at full optimism will be launched in 2016.
 
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First Light Images from Ultraviolet Imaging Telescope (UVIT) payload onboard ASTROSAT in Orbit
Ultraviolet Imaging Telescope (UVIT) is the long wavelength eye of the multi- wavelength satellite ASTROSAT, which carries telescopes giving a spectral
coverage from hard X-rays to ultraviolet. The satellite was launched on September 28, 2015. Soon after the
launch testing of the X-ray telescopes followed. The subsystems of UVIT, e.g. the detectors, were also checked with the doors closed to isolate the optics from degassing of the S/C. The doors of UVIT opened on November 30 and it was pointed to a relatively bright field at high declination and images were taken.
This note describes the impressions from these images regarding performance of the payload.
The Performance Parameters of UVIT
UVIT is configured as two Cassegrain- telescopes each of ~ 375 mm aperture. One of the telescope images in
130-180 nm (FUV) and the other images in 200-300 nm (NUV) and 320-550 nm (VIS). A suit of filters allow
further selection of a narrower.wavelength band for all the three detectors. The field is ~ 28’ in diameter
and the most important specifications for imaging are: a) spatial resolution (FWHM) of the ultraviolet images <1.8”, b) sensitivity in 130-180 nm ~ AB mag 20 in 200 s of exposure.
The Source

For the first light observations an open cluster of stars in our Galaxy, NGC 188, was chosen. This selection was based on the need to have the first pointing in
a direction well away from the equatorial plane to keep the operations of pointing simple, and to have a source which has a variety of stars but not a very high density of stars. This open cluster (a group of stars which are
gravitationally bound) is many billion years old and contains ~ 1500 stars. It is located at a distance of ~ 6000 light years in the constellation Cepheus. The
cluster has several bright stars which are easily recognisable and are suitable for a first light exposure. Though this source is not a primary standard, it has
been studied in details by the past missions so that a good idea of the performance of UVIT can be obtained
from these images. Imaging of weak sources, with the proposed resolution of 1.8”, requires corrections for the small drift of the S/C (<0.5”/s) by images obtained with the visible detector.
Therefore, in order to keep the analysis simple, it was important to have bright sources so that sensible images could be obtained in a few seconds in the
ultraviolet and used for self-correction of the drift.
Preliminary Impressions on the Performance
The images were taken for several minutes with all the three detectors; the UV detectors worked in photon-counting mode to detect each individual photon, while the visible detectors worked in integration mode (like a typical CCD- camera). As the pointing has some drift, the images are taken in short (<~ 1s) exposures and are added together after correcting for the drift. This
procedure is easily implemented for this field as bright stars (mag < 15) are available in the field. The final images are presented in the figure below.
new_picture121.png

new_picture_122.png

new_picture123.png

Figure: Final images from the FUV (top), NUV (middle), and VIS (bottom) detectors are shown. Please note that axes in the three images are not aligned but the angular coverage is nearly identical. While the UV images have been processed to correct for the drift, the VIS image has not been processed
for this. Detailed view of the bottom-most star in the FUV image is shown below. This is a very bright star and the image suffers from effects of saturation in the
detector. The central peak is immediately surrounded by a moat (which is almost devoid of any photons) and an outer ring which is outer part of the wings in PSF: this structure can be explained by the effects of saturation when the average photon rate exceeds one per exposure.
new_picture124.png

Distribution along X-axis in the Central
peak of the image is shown below.
Each division on the X-axis is ~ 1.6”
wide, and scale on the Y-axis shows
brightness on a linear scale.
new_picture1275.png

The recorded counts of the photons in
the FUV detector show that sensitivity
of the FUV channel is as per the
expectation.
Conclusion
This analysis of the first light images suggests that the most important performance-parameters of UVIT (PSF
and FUV-sensitivity) meet the expectations. More observations for the calibrations and more rigorous analysis of the data would follow for full characterisation of the payload. We look forward to flood of excellent results on ultraviolet astronomy of stars, clusters, galaxies etc..
UVIT project is a collaborative effort of IIA (Bengaluru), IUCAA (Pune), TIFR(Mumbai), and ISRO from India, and CSA of Canada.

@gslv mk3
@Echo_419
 
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