Augmented Satellite Launch Vehicle

Augmented Satellite Launch Vehicle
Function	Small carrier rocket
Manufacturer	ISRO
Country of origin	India
Size
Height	24 metres (79 ft)
Diameter	1 metre (3.3 ft)
Mass	41,000 kilograms (90,000 lb)
Capacity
Payload to 400km LEO	150 kilograms (330 lb)
Associated rockets
Family	SLV, PSLV, GSLV
Launch history
Status	Retired
Launch sites	Sriharikota
Total launches	4
Successes	1
Failures	2
Partial failures	1
Maiden flight	24 March 1987
Last flight	4 May 1994
Notable payloads	SROSS
First Stage
Engines	2 solid
Thrust	502.6 kilonewtons (113,000 lbf) each
Specific impulse	253 sec
Burn time	49 seconds
Fuel	Solid
Second Stage
Engines	1 solid
Thrust	702.6 kilonewtons (158,000 lbf)
Specific impulse	259 sec
Burn time	45 seconds
Fuel	Solid
Third Stage
Engines	1 solid
Thrust	304 kilonewtons (68,000 lbf)
Specific impulse	276 sec
Burn time	36 seconds
Fuel	Solid
Fourth Stage
Engines	1 solid
Thrust	90.7 kilonewtons (20,400 lbf)
Specific impulse	277 sec
Burn time	45 seconds
Fuel	Solid
Fifth Stage
Engines	1 solid
Thrust	35 kilonewtons (7,900 lbf)
Specific impulse	281 sec
Burn time	33 seconds
Fuel	Solid

The Augmented Satellite Launch Vehicle (संवर्धित उपग्रह प्रक्षेपण यान) or Advanced Satellite Launch Vehicle, also known as ASLV, was a five-stage solid propellant rocket developed by the Indian Space Research Organisation (ISRO) to place 150 kg satellites into LEO.^[1] This project was started by India during the early 1980s to develop technologies needed for a payload to be placed into a geostationary orbit.^[2] Its design was based on Satellite Launch Vehicle.^[3] ISRO did not have sufficient funds for both the PSLV programme and the ASLV programme at the same time and the ASLV programme was terminated after the initial developmental flights.^[2] The payloads of ASLV were Stretched Rohini Satellites.^[3]

Vehicle[link]

The ASLV was not a simple variant of the earlier SLV but a more complex vehicle; a five-stage vehicle with the core stage not igniting until the two strap-on first stage boosters burn out. The payload capacity of the ASLV is approximately 150 kg to an orbit of 400 km with a 47-degree inclination.^[3]

At liftoff, the ASLV generated 92,780 kgf of thrust. It was a 41,000 kilogram rocket, measuring 23.5 metres in length with a core diameter of one metre.^[3]

History[link]

The ASLV made four launches, of which one was successful, two failed to achieve orbit, and a fourth achieved a lower than planned orbit which decayed quickly. The type made its maiden flight on 24 March 1987, and its final flight on 4 May 1994.

Three successive failures plunged the project into a crisis. ISRO scientist had to confront new technological challenges and one of the important design changes was the addition of the 2 strap on boosters attached to either side of the first stage. Strap on separation, bulbous heat shield, "closed loop" guidance system as opposed to the "open loop" guidance system of the SLV-3 and heat shield management and separation had to be adapted by the scientists. However, all the problems and new technological challenges were overcome with ISRO's customary resolve and zeal, and the important ASLV program crossed an important rubicon.^{[citation needed]}

Launch log[link]

All four ASLV launches were conducted from the First Launch Pad at Sriharikota.

See also[link]

• Comparison of orbital launchers families

References[link]

v t e Expendable launch systems Current Spaceflight portal Ariane 5 Atlas V Delta II IV Dnepr-1 GSLV H-IIA H-IIB Kaituozhe-1 Kosmos-3M Long March 1D 2C 2D 2F 3A 3B 3C 4B 4C Minotaur I IV Naro-1 Paektusan Pegasus Proton-M PSLV Rokot Safir Shavit Shtil' Start-1 Strela Soyuz U FG 2 Taurus Tsyklon-2 Unha Vega VLS-1 Volna Zenit 2 2M 3SL 3SLB 3F Planned Angara Antares Athena Ic IIc Ausroc IV Epsilon GSLV III Haas Long March 5 6 7 Minotaur V Naro-2 Rocket Lab RPS (420, 550) Simorgh SLS Southern Cross Soyuz-2-1v SPARK Tsyklon-4 VLM VLS-Alfa VLS-Beta Previous Ariane 1 2 3 4 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able Agena Centaur Black Arrow Conestoga Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 III Diamant Energia Europa Falcon 1‡ Feng Bao 1 H-I H-II J-I Juno I Juno II Kosmos 1 2I 3 Lambda 4S Long March 1 2A 2E 3 4A Mu 4S 3C 3H 3S 3SII V) N1 N-I N-II Pilot Proton UR-500 K R-7 Luna Molniya M Polyot Soyuz L M U2 Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M Saturn I IB V INT-21 Scout SLV Sparta Thor Able Ablestar Agena Burner Delta DSV-2U Thorad-Agena Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon 3 Vanguard ‡ – Falcon 1 was designed for partial reuse. However, recovery failed on the first three flights and the remaining vehicles were flown expendably.

Kamiokisihkwew in 1896

Fineday or Kamiokisihkwew (born ca. 1852 – unknown; but after 1935) was a Cree war chief of the River People band of Plains Cree. He participated in the North-West Rebellion of 1885 (notably the battle of Cut Knife). Described by a contemporary as "brave in all things," he was a skilled warrior, hunter, trapper and (in later life) a powerful shaman.^[1]

Fineday's memories of the North West rebellion were published by the Canadian North-West Historical Society in 1926.^[2]

David G. Mandelbaum, in the introduction to his extensive study of the Plains Cree cites Fineday as his principal informant.

References[link]

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