A launch vehicle or bearer rocket is a rocket-push vehicle used to convey a payload from Earth's surface to space, generally to Earth orbit or ahead. A dispatch framework incorporates the launch vehicle, platform, vehicle gathering and fuelling frameworks, field security, and other related bases.
Orbital launch vehicles can be gathered depending on various variables, most especially payload mass, even though value focuses are a significant concern for certain clients. Most of these have been built by or for national space programs, with impressive national glory joined to spaceflight achievements. Payloads incorporate maintained shuttle, satellites, automated rockets, logical tests, landers, drifters, and many more.
First Generation Launchers:
These launchers have two classifications:
Sounding Rockets: Sounding rockets are normally one or two stages strong force rockets. They are fundamentally planned for examining the upper meteorological areas utilizing rocket-borne instrumentation. They likewise fill in as stages for testing models of new segments or subsystems expected for use in launch vehicles and satellites. The dispatch of the primary sounding rocket US-made 'Nike Apache' from Thumba close Thiruvananthapuram, Kerala on November 21, 1963, denoted the start of the Indian Space Program.
Operational Sounding Rockets: As of now, operational sounding rockets incorporate three forms termed RH-200, RH-300-Mk-II and RH-560-Mk-III. These spread a payload scope of 8 to 100 kg and an apogee scope of 80 to 475 km.
Operational sounding rockets are separated among two class:
The Satellite Launch Vehicle (SLV): The Satellite Launch Vehicle venture was conceived out of the requirement for accomplishing indigenous satellite dispatch capacity for interchanges, remote detecting and meteorology. SLV3, India's first test launch vehicle, was fit for setting 40 kg class payloads in Low Earth Orbit (LEO). It was an all strong, four phases, 22m tall vehicle, and gauging 17 tons.
The Augmented Satellite Launch Vehicle (ASLV): Augmented Satellite Launch Vehicle was created to go about as an economical transitional vehicle to exhibit and approve basic advances.
Operational Launchers are partitioned into two arrangements:
Polar Satellite Launch Vehicle (PSLV): The primary operational launch vehicle of ISRO is the Polar Satellite Launch Vehicle. PSLV is fit for propelling 1600 kg satellites in 620 km sun-identical polar orbit and 1050 kg satellite in geo-synchronous exchange orbit.
Geosynchronous Satellite Launch Vehicle (GSLV): Geosynchronous Satellite Launch Vehicle (GSLV) is equipped for putting 2 ton class of satellites like the INSAT and GSAT sequence of communication satellites into Geosynchronous Transfer Orbit (GTO).
Next Generation Launchers:
Geosynchronous Satellite Launch Vehicle Mark III is the next generation launch vehicle being created for achieving self-reliance in the dispatch of 4 ton class of communication satellites to Geosynchronous Transfer Orbits (GTO).
ASLV was 24m tall launch vehicle with a lift-off weight of 40 tons and was constructed as a five-phase, all-sturdy force vehicle, to rotate 150 kg class satellites into 400 km round orbits.
The Augmented Satellite Launch Vehicle Program was intended to enlarge the payload ability to 150 kg, threefold that of SLV-3, for Low Earth Orbits (LEO). While constructing upon the experience picked up from the SLV-3 missions, ASLV ends up being a minimal effort transitional vehicle to show and approve demanding advances, that would be required for the future launch vehicles, like, a leash on technology, inertial route, bulbous warmth shield, vertical mix and closed-loop direction.
Under the ASLV program, four preliminary flights were directed. The principal developmental flight occurred on March 24 1987, and the second on July 13, 1988. The third developmental flight, ASLV-D3 was effectively launched on May 20, 1992, when, SROSS-C (106 kg) was placed into an orbit of 255 x 430 km. ASLV-D4 propelled on May 4, 1994, orbited SROSS-C2 weighing 106 kg. It had two payloads, Gamma Ray Burst (GRB) Experiment and Retarding Potential Analyser (RPA) and worked for about seven years.
Classic parameters of ASLV are:
Height of ASLV - 23.8m
Weight of ASLV - 40 tonnes
Fuel - Solid
Payload Mass - 150kg
Orbit - Low Earth (400km Circular Orbits)
1. Why PSLV is Used?
Ans: PSLV is utilized for conveying different satellites to Low Earth Orbits. It is planned for the most part to convey the "earth-inspection" or "remote-detecting" satellites; with a lift-off mass of up to around 1750 kg to Sun-Synchronous spheroid polar orbits of 600-900 km height.
2. What is the Meaning of PSLV?
Ans: PSLV, the Polar Satellite Launch Vehicle, was created to empower India to dispatch its Indian Remote Sensing (IRS) satellites into Sun-coordinated orbits. It can likewise be utilized to dispatch small size satellites into geostationary transfer orbit (GTO).
3. What Type of Fuel is Utilised by GSLV for Operating?
Ans: In case of the GSLV Mk III's cryogenic stage, which is entitled C25 and utilizes a CE-20 motor, these fuels are liquid oxygen and liquid hydrogen, are the most commonly recognized energies utilized for such engines.
4. What is ASLV in Simple Words?
Ans: ASLV was a Small-lift launch vehicle which was a five-phase strong fuel rocket created by the Indian Space Research Organization (ISRO) to put 150 kg satellites into LEO.