53-728: PSLV-C38 was the 40th mission of the Indian Polar Satellite Launch Vehicle (PSLV) program and its 17th mission in the XL configuration. PSLV-C38 successfully carried and deployed 31 satellites in Sun-synchronous orbit . It was launched on 23 June 2017 by the Indian Space Research Organisation (ISRO) from the Satish Dhawan Space Centre at Sriharikota , Andhra Pradesh . PSLV-C38 carried
106-413: A > 12 352 km . If one wants a satellite to fly over some given spot on Earth every day at the same hour, the satellite must complete a whole number of orbits per day. Assuming a circular orbit, this comes down to between 7 and 16 orbits per day, as doing less than 7 orbits would require an altitude above the maximum for a Sun-synchronous orbit, and doing more than 16 would require an orbit inside
159-573: A Kevlar - polyamide fibre case and a submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle with ±2° thrust vector for pitch and yaw control. Roll control is provided by the fourth stage reaction control system (RCS) during thrust phase as well as during combined-coasting phase under which burnt-out PS3 remains attached to PS4. The fourth stage is powered by regeneratively cooled twin engines, burning monomethylhydrazine (MMH) and mixed oxides of nitrogen (MON). Each pressure fed engine generates 7.4 kN (1,700 lb f ) thrust and
212-422: A toroidal tank at its bottom. Water spray is used to cool hot gases from Vikas' gas generator to about 600 °C before entering turbopump. Propellant and water tanks of second stage are pressurized by Helium . The third stage uses 7.6 t (7.5 long tons; 8.4 short tons) of HTPB solid propellant and produces a maximum thrust of 250 kN (56,000 lb f ). Its burn duration is 113.5 seconds. It has
265-598: A common bulkhead. It generates a maximum thrust of 800 kN (180,000 lb f ). The engine is gimbaled (±4°) in two planes to provide pitch and yaw control by two actuators, while roll control is provided by a Hot gas Reaction Control Motor (HRCM) that ejects hot gases diverted from gas generator of Vikas engine. On inter-stage (1/2U) of PS2 there are two pairs of ullage rockets to maintain positive acceleration during PS1/PS2 staging and also two pairs of retro-rockets to help push away spent stage during PS2/PS3 staging. Second stage also carries some quantity of water in
318-408: A demonstration PS4 was kept operational and monitored for over ten orbits after delivering spacecraft. PSLV-C44 was the first campaign where PS4 functioned as independent orbital platform for short duration as there was no on-board power generation capacity. It carried KalamSAT-V2 as a fixed payload, a 1U cubesat by Space Kidz India based on Interorbital Systems kit. On PSLV-C45 campaign,
371-465: A joint venture. On 16 August 2019, NewSpace India Limited issued an invitation to tender for manufacturing PSLV entirely by private industries. On 5 September 2022, NewSpace India Limited signed a contract with Hindustan Aeronautics Limited and Larsen & Toubro led conglomerate for the production of five PSLV-XL launch vehicles after they won competitive bidding. Under this contract, they have to deliver their first PSLV-XL within 24 months and
424-494: A leading provider of rideshare services for small satellites, owing to its numerous multi-satellite deployment campaigns with auxiliary payloads, usually ride-sharing along with an Indian primary payload. As of June 2022, PSLV has launched 345 foreign satellites from 36 countries. Most notable among these was the launch of PSLV-C37 on 15 February 2017, successfully deploying 104 satellites in Sun-synchronous orbit, tripling
477-599: A nearly continuous view of the Sun. A Sun-synchronous orbit is achieved by having the osculating orbital plane precess (rotate) approximately one degree eastward each day with respect to the celestial sphere to keep pace with the Earth's movement around the Sun . This precession is achieved by tuning the inclination to the altitude of the orbit (see Technical details ) such that Earth's equatorial bulge , which perturbs inclined orbits, causes
530-533: A partial failure in 1997, leaving its payload in a lower than planned orbit. In November 2014, the PSLV had launched 34 times with no further failures. (Although launch 41: August 2017 PSLV-C39 was unsuccessful. ) PSLV continues to support Indian and foreign satellite launches especially for low Earth orbit (LEO) satellites. It has undergone several improvements with each subsequent version, especially those involving thrust, efficiency as well as weight. In November 2013, it
583-484: A service that was, until the advent of the PSLV in 1993, only commercially available from Russia. PSLV can also launch small size satellites into Geostationary Transfer Orbit (GTO). Some notable payloads launched by PSLV include India's first lunar probe Chandrayaan-1 , India's first interplanetary mission , Mars Orbiter Mission (Mangalyaan), India's first space observatory , Astrosat and India's first Solar mission , Aditya-L1 . PSLV has gained credibility as
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#1732891315070636-538: A success rate of 95% (or 97% including the partial failure). All launches have occurred from the Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range (SHAR). Sun-synchronous orbit A Sun-synchronous orbit ( SSO ), also called a heliosynchronous orbit , is a nearly polar orbit around a planet, in which the satellite passes over any given point of the planet's surface at
689-463: Is aided by four pairs of retro-rockets installed on inter-stage (1/2L). During staging, these eight rockets help push away the spent stage away from second stage. The second stage is powered by a single Vikas engine and carries 41.5 t (40.8 long tons; 45.7 short tons) of Earth store-able liquid propellant – unsymmetrical dimethylhydrazine (UDMH) as fuel and nitrogen tetroxide (N 2 O 4 ) as oxidiser in two tanks separated by
742-597: Is expected to be replaced by lighter, silicon carbide coated carbon–carbon nozzle divergent. The new nozzle was hot tested at facilities of IPRC, Mahendragiri in March and April 2024. This substitution should increase payload capacity of PSLV by 15 kilograms (33 lb). ISRO successfully completed 665-second hot test of 3D printed PS4 engine, produced by Wipro 3D through selective laser melting . A total of 19 weld joints were eliminated through this process while engine's 14 components were reduced to one piece. It saved 60% of
795-425: Is gimbaled (±3°) to provide pitch, yaw and roll control during powered flight. Coast phase attitude control is provided by six 50N RCS thrusters. The stage is pressurized by Helium and carries 1,600 kg (3,500 lb) to 2,500 kg (5,500 lb) of propellant depending on the mission requirements. PS4 has three variants L1.6, L2.0 and L2.5 based on propellant tank capacity. On PSLV-C29/TeLEOS-1 mission,
848-580: Is made of maraging steel and has an empty mass of 30,200 kg (66,600 lb). Pitch and yaw control during first stage flight is provided by the Secondary Injection Thrust Vector Control (SITVC) System, which injects an aqueous solution of strontium perchlorate into the S139 exhaust divergent from a ring of 24 injection ports to produce asymmetric thrust. The solution is stored in two cylindrical aluminium tanks strapped to
901-517: Is made out of 7075 aluminum alloy with a 3 mm thick steel nose-cap. The two halves of fairing are separated using a pyrotechnic device based jettisoning system consisting of horizontal and lateral separation mechanisms. To protect the spacecraft from damage due to excessive acoustic loads during launch, the heatshield interior is lined with acoustic blankets. ISRO has envisaged a number of variants of PSLV to cater to different mission requirements. There are currently two operational versions of
954-399: Is nearly the same. This consistent lighting is a useful characteristic for satellites that image the Earth's surface in visible or infrared wavelengths, such as weather and spy satellites, and for other remote-sensing satellites, such as those carrying ocean and atmospheric remote-sensing instruments that require sunlight. For example, a satellite in Sun-synchronous orbit might ascend across
1007-609: Is planned to use a GSLV, modified by replacing it's Cryogenic Upper Stage(CUS) with the PS-4 as the RLV would not required the excess thrust created by the CUS. Payload fairing of PSLV, also referred as its "Heatshield" consists of a conical upper section with spherical nose-cap, a cylindrical middle section and a lower boat-tail section. Weighing 1,182 kilograms (2,606 lb), it has 3.2 meter diameter and 8.3 meter height. It has Isogrid construction and
1060-619: The PSLV-C53 campaign, the PS4-OP is referred to as the PSLV Orbital Experimental Module (POEM) , and it hosted six payloads. POEM was the first PSLV fourth stage based orbital platform to be actively stabilised using Helium based cold gas thrusters after the primary mission and stage passivization. The Reusable Launch Vehicle Technology Demonstration program is an prototype spaceplane project currently being processed by ISRO.It
1113-620: The United Kingdom were also launched. The NIUSAT satellite, weighing around 15 kg (33 lb), was prepared as a collaborative work by over 200 students of the Noorul Islam University , Kanyakumari and is used for disaster management and crop monitoring. The work on the satellite began in 2007 and cost ₹ 37 crore (US$ 4.4 million) with help from ISRO. It was conceived by University's chancellor A. P. Majeed Khan post 2004 Indian Ocean tsunami disaster . Minister of State in
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#17328913150701166-537: The terminator between day and night. Riding the terminator is useful for active radar satellites, as the satellites' solar panels can always see the Sun, without being shadowed by the Earth. It is also useful for some satellites with passive instruments that need to limit the Sun's influence on the measurements, as it is possible to always point the instruments towards the night side of the Earth. The dawn/dusk orbit has been used for solar-observing scientific satellites such as TRACE , Hinode and PROBA-2 , affording them
1219-519: The CA variant has 400 kg (880 lb) less propellant when compared to its standard version. It currently has capability to launch 1,100 kg (2,400 lb) to 622 km (386 mi) Sun-synchronous orbit . PSLV-XL is the upgraded version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful, stretched strap-on boosters with 12 tonne propellant load. Weighing 320 t (310 long tons; 350 short tons) at lift-off,
1272-488: The Earth surface. Even if an orbit remains Sun-synchronous, however, other orbital parameters such as argument of periapsis and the orbital eccentricity evolve, due to higher-order perturbations in the Earth's gravitational field, the pressure of sunlight, and other causes. Earth observation satellites, in particular, prefer orbits with constant altitude when passing over the same spot. Careful selection of eccentricity and location of perigee reveals specific combinations where
1325-401: The Earth's atmosphere or surface. The resulting valid orbits are shown in the following table. (The table has been calculated assuming the periods given. The orbital period that should be used is actually slightly longer. For instance, a retrograde equatorial orbit that passes over the same spot after 24 hours has a true period about 365 / 364 ≈ 1.0027 times longer than
1378-620: The Indian mapping satellite Cartosat-2E as its main payload that weighed 712 kg (1,570 lb). 30 smaller satellites were carried as secondary payload, among them the Indian university NIUSAT monitoring satellite, Japanese CE-SAT1 technology demonstrator, Austrian AT-03 Pegasus research satellite and American CICERO-6 weather satellite. Satellites of Belgium , Chile , the Czech Republic VZLUSat-1 , Finland , France , Germany , Italy , Latvia , Lithuania , Slovakia SkCube , and
1431-495: The PSLV Planning group under S Srinivasan to develop a vehicle capable of delivering a 600 kg payload to a 550 km sun-synchronous orbit from SHAR began in 1978. Among 35 proposed configurations, four were picked; by November 1980, a vehicle configuration with two strap-ons on a core booster (S80) with 80 tonne solid propellant loading each, a liquid stage with 30 tonne propellant load (L30), and an upper stage called
1484-725: The PSLV — the core-alone (PSLV-CA) without strap-on motors, and the (PSLV-XL) version, with six extended length (XL) strap-on motors carrying 12 tonnes of HTPB based propellant each. These configurations provide wide variations in payload capabilities up to 3,800 kg (8,400 lb) in LEO and 1,800 kg (4,000 lb) in sun-synchronous orbit. The standard or "Generic" version of the PSLV, PSLV-G had four stages using solid and liquid propulsion systems alternately and six strap-on motors (PSOM or S9) with 9 tonne propellant loading. It had capability to launch 1,678 kg (3,699 lb) to 622 km (386 mi) into sun-synchronous orbit. PSLV-C35
1537-480: The Perigee-Apogee System (PAS) was being considered. By 1981, confidence grew in remote sensing spacecraft development with the launch of Bhaskara-1 , and the PSLV project objectives were upgraded to have the vehicle deliver a 1000 kg payload into a 900 km SSO . As technology transfer of Viking rocket engine firmed up, a new lighter configuration with the inclusion of a liquid powered stage
1590-535: The Prime Minister's Office Jitendra Singh stated that ISRO earned ₹ 45.2 crore (EUR 6.1 million) from launching foreign satellites on PSLV-C38. Polar Satellite Launch Vehicle The Polar Satellite Launch Vehicle ( PSLV ) is an expendable medium-lift launch vehicle designed and operated by the Indian Space Research Organisation (ISRO). It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into Sun-synchronous orbits ,
1643-827: The core solid rocket motor and pressurised with nitrogen . Underneath these two SITVC tanks, Roll Control Thruster (RCT) modules with small bi-propellant (MMH/MON) liquid engine are also attached. On the PSLV-G and PSLV-XL, first stage thrust is augmented by six strap-on solid boosters . Four boosters are ground-lit and the remaining two ignite 25 seconds after launch. The solid boosters carry 9 t (8.9 long tons; 9.9 short tons) or 12 t (12 long tons; 13 short tons) (for PSLV-XL configuration) propellant and produce 510 kN (110,000 lb f ) and 719 kN (162,000 lb f ) thrust respectively. Two strap-on boosters are equipped with SITVC for additional attitude control. The PSLV-CA uses no strap-on boosters. First stage separation
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1696-466: The direction of Earth's rotation: 0° represents an equatorial orbit, and 90° represents a polar orbit. Sun-synchronous orbits are possible around other oblate planets, such as Mars . A satellite orbiting a planet such as Venus that is almost spherical will need an outside push to maintain a Sun-synchronous orbit. The angular precession per orbit for an Earth orbiting satellite is approximately given by where An orbit will be Sun-synchronous when
1749-414: The earth. As the orbital period of a spacecraft is where a is the semi-major axis of the orbit, and μ is the standard gravitational parameter of the planet ( 398 600 .440 km /s for Earth); as p ≈ a for a circular or almost circular orbit, it follows that or when ρ is 360° per year, As an example, with a = 7200 km , i.e., for an altitude a − R E ≈ 800 km of
1802-405: The equator twelve times a day, each time at approximately 15:00 mean local time. Special cases of the Sun-synchronous orbit are the noon/midnight orbit , where the local mean solar time of passage for equatorial latitudes is around noon or midnight, and the dawn/dusk orbit , where the local mean solar time of passage for equatorial latitudes is around sunrise or sunset, so that the satellite rides
1855-508: The fourth stage demonstrated re-ignition capability for the first time which was used in many subsequent flights to deploy payloads in multiple orbits on a single campaign. As a space debris mitigation measure, PSLV fourth stage gets passivated by venting pressurant and propellant vapour after achieving main mission objectives. Such passivation prevents any unintentional fragmentation or explosion due to stored internal energy. The niobium alloy nozzle used on twin engines of fourth stage
1908-530: The fourth stage had its own power generation capability as it was augmented with an array of fixed solar cells around PS4 propellant tank. The three payloads hosted on PS4-OP were the Advanced Retarding Potential Analyzer for Ionospheric Studies (ARIS 101F) by IIST , an experimental AIS payload by ISRO, and AISAT by Satellize . To function as orbital platform, fourth stage was put in spin-stabilized mode using its RCS thrusters. On
1961-408: The orbital plane of the spacecraft to precess with the desired rate. The plane of the orbit is not fixed in space relative to the distant stars, but rotates slowly about the Earth's axis. Typical Sun-synchronous orbits around Earth are about 600–800 km (370–500 mi) in altitude, with periods in the 96–100- minute range, and inclinations of around 98°. This is slightly retrograde compared to
2014-405: The precession rate ρ = d Ω / d t equals the mean motion of the Earth about the Sun n E , which is 360° per sidereal year ( 1.990 968 71 × 10 rad /s ), so we must set n E = Δ Ω E / T E = ρ = Δ Ω / T , where T E is the earth orbital period while T is the period of the spacecraft around
2067-481: The previous record held by Russia for the highest number of satellites sent to space on a single launch, until 24 January 2021, when SpaceX launched the Transporter-1 mission on a Falcon 9 rocket carrying 143 satellites into orbit. Payloads can be integrated in tandem configuration employing a Dual Launch Adapter. Smaller payloads are also placed on equipment deck and customized payload adapters. Studies by
2120-550: The production time and drastically decreased the amount of raw materials used per engine, from 565 kg to 13.7 kg of metal powder. PS4 has carried hosted payloads like AAM on PSLV-C8, Rubin 9.1 / Rubin 9.2 on PSLV-C14 and mRESINS on PSLV-C21. But now, PS4 is being augmented to serve as a long duration orbital platform after completion of primary mission. PS4 Orbital Platform (PS4-OP) will have its own power supply, telemetry package, data storage and attitude control for hosted payloads. On PSLV-C37 and PSLV-C38 campaigns, as
2173-457: The remaining four vehicles every six months. The PSLV has four stages, using solid and liquid propulsion systems alternately. The first stage, one of the largest solid rocket boosters in the world, carries 138 t (136 long tons; 152 short tons) of hydroxyl-terminated polybutadiene -bound (HTPB) propellant and develops a maximum thrust of about 4,800 kN (1,100,000 lb f ). The 2.8 m (9 ft 2 in) diameter motor case
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2226-410: The same local mean solar time . More technically, it is an orbit arranged so that it precesses through one complete revolution each year, so it always maintains the same relationship with the Sun. A Sun-synchronous orbit is useful for imaging , reconnaissance , and weather satellites , because every time that the satellite is overhead, the surface illumination angle on the planet underneath it
2279-530: The second and fourth stages of the PSLV as well as the Reaction control systems (RCS) are developed by the Liquid Propulsion Systems Centre (LPSC) at Valiamala near Thiruvananthapuram , kerala . The solid propellant motors are processed at Satish Dhawan Space Centre (SHAR) at Sriharikota , Andhra Pradesh , which also carries out launch operations. The aerodynamic characterization research
2332-524: The solid terminal stage (S2) was replaced with a pressure fed liquid fueled stage (L1.8 or LUS) powered by twin engines derived from roll control engines of the first stage. Apart from increasing precision, liquid upper stage also absorbed any deviation in performance of solid third stage. The final configuration of PSLV-D1 to fly in 1993 was (6 × S9 + S125) + L37.5 + S7 + L2. The inertial navigation systems are developed by ISRO Inertial Systems Unit (IISU) at Thiruvananthapuram . The liquid propulsion for
2385-590: The spacecraft over Earth's surface, this formula gives a Sun-synchronous inclination of 98.7°. Note that according to this approximation cos i equals −1 when the semi-major axis equals 12 352 km , which means that only lower orbits can be Sun-synchronous. The period can be in the range from 88 minutes for a very low orbit ( a = 6554 km , i = 96°) to 3.8 hours ( a = 12 352 km , but this orbit would be equatorial, with i = 180°). A period longer than 3.8 hours may be possible by using an eccentric orbit with p < 12 352 km but
2438-532: The time between overpasses. For non-equatorial orbits the factor is closer to 1.) When one says that a Sun-synchronous orbit goes over a spot on the Earth at the same local time each time, this refers to mean solar time , not to apparent solar time . The Sun will not be in exactly the same position in the sky during the course of the year (see Equation of time and Analemma ). Sun-synchronous orbits are mostly selected for Earth observation satellites , with an altitude typically between 600 and 1000 km over
2491-489: The vehicle uses larger strap-on motors (PSOM-XL or S12) to achieve higher payload capability. On 29 December 2005, ISRO successfully tested the improved version of strap-on booster for the PSLV. The first use of PSLV-XL was the launch of Chandrayaan-1 by PSLV-C11. The payload capability for this variant is 1,800 kg (4,000 lb) to Sun-synchronous orbit. PSLV-DL variant has only two strap-on boosters with 12 tonne propellant load on them. PSLV-C44 on 24 January 2019
2544-444: Was conceived as a three-staged version of PSLV with its six strap-on boosters and second liquid stage removed. The total lift-off mass of PSLV-3S was expected to be 175 tonnes with capacity to place 500 kg in 550 km low Earth orbit . PSLV - XL: As of 1 January 2024 the PSLV has made 60 launches, with 57 successfully reaching their planned orbits, two outright failures and one partial failure, yielding
2597-535: Was conducted at the National Aerospace Laboratories ' 1.2m Trisonic Wind Tunnel Facility. The PSLV was first launched on 20 September 1993. The first and second stages performed as expected, but an attitude control problem led to the collision of the second and third stages at separation, and the payload failed to reach orbit. After this initial setback, the PSLV successfully completed its second mission in 1994. The fourth launch of PSLV suffered
2650-496: Was selected. Funding was approved in July 1982 for the finalized design, employing a single large S125 solid core as first stage with six 9 tonne strap-ons (S9) derived from the SLV-3 first stage, liquid fueled second stage (L33), and two solid upper stages (S7 and S2.) This configuration needed further improvement to meet the orbital injection accuracy requirements of IRS satellites, and hence,
2703-468: Was the first flight to use PSLV-DL variant of Polar Satellite Launch Vehicle. It is capable of launching 1,257 kg (2,771 lb) to 600 km (370 mi) Sun-synchronous orbit. PSLV-QL variant has four ground-lit strap-on boosters, each with 12 tonnes of propellant. PSLV-C45 on 1 April 2019 was the first flight of PSLV-QL. It has the capacity to launch 1,523 kg (3,358 lb) to 600 km (370 mi) Sun-synchronous orbit. PSLV-3S
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#17328913150702756-423: Was the last operational launch of PSLV-G before its discontinuation. The PSLV-CA , CA meaning "Core Alone", model premiered on 23 April 2007. The CA model does not include the six strap-on boosters used by the PSLV standard variant but two SITVC tanks with Roll Control Thruster modules are still attached to the side of the first stage with addition of two cylindrical aerodynamic stabilizers. The fourth stage of
2809-529: Was used to launch the Mars Orbiter Mission , India's first interplanetary probe. In June 2018, the Union Cabinet approved ₹ 6,131 crore (equivalent to ₹ 72 billion or US$ 860 million in 2023) for 30 operational flights of the PSLV scheduled to take place between 2019 and 2024. ISRO is working towards handing over the production and operation of PSLV to private industry through
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