ISRO started it's project of SLV in early 1970s. this project was headed by A.P.J Abdul kalam. a satellite launch vehicle is used for launching of satellite. this project had its first experimental flight of SLV-3 in August 1979 which was partially successful. but now india has a capacity to design, manufacture and launch it's own satellite. thanks to the hard and dedicated work of ISRO.
Read the passage and answer the following questions
(a) On what principle does a SLV work?
(b) Explain the above principle for SLV.
(c )Can this principle work in vacuum or space?
(d) Name the Newton law of motion used in this principal
(e) What are the values displayed by ISRO?
Answers
Answer:
The Satellite Launch Vehicle or SLV was a small-lift launch vehicle project started in the early 1970s by the Indian Space Research Organisation to develop the technology needed to launch satellites.
...
Satellite Launch Vehicle.
Size
Altitude 400 km (250 mi)
Mass 40 kg (88 lb)
Associated rockets
Derivatives ASLV, PSLV
50 more rows
Answer:
The Satellite Launch Vehicle or SLV was a small-lift launch vehicle project started in the early 1970s by the Indian Space Research Organisation to develop the technology needed to launch satellites. SLV was intended to reach a height of 400 kilometres (250 mi) and carry a payload of 40 kg (88 lb).[2] The first experimental flight of SLV-3, in August 1979, was a failure.[3] The first successful launch took place on 18 July, 1980.
Satellite Launch Vehicle
SatLaunchVehicle.jpeg
Satellite Launch Vehicle
Function
Small-lift launch vehicle
Manufacturer
ISRO
Country of origin
India
Size
Height
22 m (72 ft)
Diameter
1 m (3.3 ft)
Mass
17,000 kg (37,000 lb)
Capacity
Payload to LEO
Altitude
400 km (250 mi)
Mass
40 kg (88 lb)
Associated rockets
Derivatives
ASLV, PSLV
Launch history
Status
Retired
Launch sites
Sriharikota
Total launches
4
Success(es)
2
Failure(s)
1
Partial failure(s)
1
First flight
10 August 1979
Last flight
17 April 1983
Notable payloads
Rohini
First stage
Propellant mass
8.6 t (19,000 lb)
Engines
1 solid
Thrust
450 kN (100,000 lbf)
Specific impulse
253 seconds (2.48 km/s)
Burn time
49 seconds
Fuel
PBAN (Polybutadine Acrylo Nitrate) Solid[1]
Second stage
Propellant mass
3 tonnes
Engines
1 solid
Thrust
20 tonnes
Specific impulse
267 sec
Burn time
40 seconds
Fuel
PBAN (Polybutadine Acrylo Nitrate)Solid
Third stage
Propellant mass
1 tonnes
Engines
1 solid
Thrust
6.3 tonnes
Specific impulse
277 sec
Burn time
45 seconds
Fuel
high energy propellant (HEF 20)Solid
Fourth stage
Propellant mass
262 kg
Engines
1 solid
Thrust
2.4 tonnes
Specific impulse
283 sec
Burn time
33 seconds
Fuel
high energy propellant (HEF 20)Solid
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