Fact-checked by Grok 2 weeks ago

ISRO Propulsion Complex

The ISRO Propulsion Complex (IPRC) is a premier testing and integration facility of the (), situated at Mahendragiri Hills in the of , , specializing in the research, development, assembly, and qualification of liquid propulsion systems for launch vehicles and . Formerly known as the , Mahendragiri (LPSC-M), IPRC was established to support 's growing needs in advanced propulsion technologies, evolving from earlier liquid propulsion test facilities operational since the 1980s as part of LPSC's expansion for cryogenic and storable propellant systems. The complex plays a critical role in ensuring the reliability and performance of propulsion stages, including high-altitude and vacuum simulations for upper-stage engines and thrusters, while supplying storable liquid propellants for 's launch vehicles such as the (PSLV) and (GSLV), as well as satellite programs. IPRC's state-of-the-art infrastructure includes specialized test stands for cold flow and hot-fire testing of earth-storable, cryogenic, and semi-cryogenic engines, along with facilities like the Semi-cryogenic Cold Flow Test (SCFT) setup for subsystem qualification. It supports key missions by developing and testing components for inter-planetary explorations and initiatives, such as the program, where it conducted successful hot tests of the Service Module Propulsion System (SMPS) in July 2025 using bi-propellant configurations. Notable achievements at IPRC include the realization of indigenous cryogenic engines, such as the 75 kN throttleable for GSLV and the 200 kN for the Launch Vehicle Mark-3 (), enabling self-reliant upper-stage propulsion for heavy-lift launches. The facility has also advanced semi-cryogenic technology, conducting a short-duration hot test of a 2,000 kN using (LOX) and refined kerosene (Isrosene) in April 2025, with the Semicryogenic Integrated Engine Test (SIET) facility established in February 2024 to bolster future capabilities. Through rigorous emphasizing safety, zero defects, and reliability, IPRC continues to drive ISRO's propulsion innovations, contributing to over 100 successful launches and ongoing R&D for next-generation systems.

Overview

Location and Establishment

The ISRO Propulsion Complex (IPRC) is situated in the Mahendragiri Hills of , , , near , providing a remote and elevated terrain ideal for propulsion testing due to its isolation from populated areas and stable geological features. This location in the ensures safety during high-thrust engine tests and minimizes environmental and acoustic disturbances. Originally established as the Mahendragiri unit of the (LPSC) in the 1970s to support early liquid propulsion development, including the Vikas engine, the site focused on assembly, integration, and testing of earth-storable and cryogenic propulsion systems. It was formally elevated to an independent centre and renamed the ISRO Propulsion Complex on 1 February 2014, with the mandate to realize advanced propulsion technologies for launch vehicles and satellites. The complex employs personnel supporting comprehensive propulsion R&D activities. It also features an on-site museum that showcases ISRO's propulsion heritage through exhibits on engine development and space mission milestones.

Organizational Role and Mandate

The ISRO Propulsion Complex (IPRC) serves as a lead centre within the (ISRO), operating under the , , and reporting directly to ISRO headquarters in . It is headed by a Centre Director, currently Shri J. Asir Packiaraj, a Distinguished Scientist, who oversees operations and integrates efforts with other ISRO units, such as the (VSSC), for collaborative development and integration. This structure ensures coordinated advancement of technologies across ISRO's ecosystem. IPRC's core mandate encompasses the assembly, integration, testing, and system engineering of high-performance liquid propulsion systems, including those using earth-storable, cryogenic, semi-cryogenic, and LOX-methane propellants, for both launch vehicles and spacecraft. It is responsible for the development, qualification, and acceptance testing of subsystems, as well as the supply of storable liquid propellants to support ISRO's satellite and launch vehicle programs, such as the second stage of the Polar Satellite Launch Vehicle (PSLV). Additionally, IPRC conducts research for advancing liquid propulsion technologies tailored to satellites and launch vehicles, ensuring reliability and performance in operational environments. Strategically, IPRC plays a pivotal role in achieving self-reliance in propulsion technology as part of India's national space policy, contributing to the indigenization of critical components like cryogenic engines (e.g., 75 kN for GSLV and 200 kN for LVM3) and semi-cryogenic engines (2000 kN thrust). It supports key missions, including propulsion systems for Chandrayaan-3 and hot tests of the Gaganyaan Service Module Propulsion System, bolstering India's capabilities in inter-planetary exploration and human spaceflight. IPRC's annual budget allocation is integrated into ISRO's overall funding of approximately ₹13,500 crore for 2025-26.

History

Early Development as LPSC

Liquid propulsion development within the Indian Space Research Organisation () traces back to the 1970s, when efforts began to develop indigenous liquid propulsion technologies as part of early programs, including control thrusters and reaction control systems using hypergolic propellants for auxiliary propulsion in the Satellite Launch Vehicle-3 (SLV-3) and (ASLV). The (LPSC) was established on 1 June 1987 by merging existing liquid propulsion units, with its headquarters initially at Valiamala near and later in . A dedicated unit at Mahendragiri was set up in the late 1980s to focus on research and development of liquid propulsion systems. In the 1980s, the Mahendragiri unit played a pivotal role in adapting foreign technology for domestic use, particularly through collaboration with France's Société Européenne de Propulsion (SEP) under a 1974 agreement. This partnership facilitated the transfer of Viking engine technology, which served as the foundation for the Vikas engine—a high-thrust, turbopump-fed engine using (UDMH) and nitrogen tetroxide (N2O4). The Vikas engine's development marked a significant milestone, enabling its integration into subsequent launch vehicles and establishing Mahendragiri as a key site for static testing of propulsion components. By the late 1980s, LPSC's work at the site had progressed to support the (PSLV) program, with initial hot tests validating engine performance. The 1990s saw substantial expansion at Mahendragiri to address cryogenic , prompted by international restrictions and the need for upper-stage engines in geosynchronous missions. Initial static test stands were constructed in 1993 as part of the PSLV infrastructure, allowing for ground qualification of liquid stages under simulated flight conditions. This period also involved early R&D on cryogenic engines using and , laying the groundwork for the (GSLV) program. By the early 2000s, additional hypergolic test facilities were added to handle increased testing demands for Vikas variants and control systems, culminating in the successful qualification of the GSLV Mk I's cryogenic stage by 2001, which relied on imported hardware but was integrated and verified at Mahendragiri. These developments solidified the site's role within LPSC until its elevation to an independent centre in 2014.

Elevation to Independent Centre

On 1 February 2014, the (LPSC) unit at Mahendragiri was redesignated as the ISRO Propulsion Complex (IPRC), marking its elevation to an independent centre within the (). This transition was motivated by the need to provide better management control and a dedicated focus on assembly, integration, and testing of systems, as 's launch vehicle programs grew in complexity with demands for advanced cryogenic and semi-cryogenic technologies. The redesignation allowed IPRC to operate with greater autonomy, functioning as a separate department equipped to handle expanded responsibilities in development. Following the elevation, IPRC experienced immediate operational enhancements, including increased in budgeting and staffing to support specialized activities. This shift facilitated the integration of advanced and testing tailored for high-performance engines. The first major under the new status was the initiation of testing for the cryogenic engine, with a significant 635-second hot test conducted on 28 April 2015 at IPRC's facilities, validating its performance for upper-stage applications in heavy-lift vehicles. The elevation significantly boosted India's self-reliance in cryogenic propulsion technology, aligning with ISRO's successful demonstration of indigenous cryogenic capabilities in 2014 and broader efforts to reduce dependence on foreign suppliers.

Facilities

Principal Test Stand (PST)

The Principal Test Stand (PST) serves as a cornerstone facility at the ISRO Propulsion Complex (IPRC) for conducting static hot tests of earth-storable liquid engines and hypergolic bipropellant systems under sea-level conditions. Established in 1993, the PST features a 32-meter-tall vertical structure divided into two primary sections: the Engine Test Section, designed to accommodate single engines with thrust levels up to 800 kN, and the Stage Test Section, capable of testing complete upper stages up to 1,000 kN thrust. These capabilities enable comprehensive performance evaluation, including thrust vector control and ignition sequence validation, essential for qualifying propulsion systems prior to flight integration. The PST plays a pivotal role in the development and of the Vikas engine family, which powers the second stages of PSLV and GSLV launch vehicles, as well as similar hypergolic thrusters for attitude control and orbit maneuvers. Upgrades undertaken in the enhanced its instrumentation and safety features, allowing it to support over 15 mission qualification campaigns annually by facilitating long-duration firings and restart demonstrations. For instance, in 2023, the PST hosted a series of 14 hot tests on nine human-rated Vikas engines for the L110 stage of the program, accumulating 1,215 seconds of firing time to verify reliability under crewed mission requirements. Additionally, in July 2025, the PST supported successful hot tests of the Service Module Propulsion System (SMPS) using bi-propellant configurations. Unique to the PST are its integrated flame deflection system, which directs high-temperature exhaust gases safely away from the test article using water-cooled deflectors, and advanced setups that monitor key parameters such as , chamber , and structural vibrations in real-time. These elements ensure precise diagnostics and minimize risks during high-energy tests of storable propellants like nitrogen tetroxide and . Overall, the facility's robust design supports ISRO's focus on reliable liquid propulsion for operational launch vehicles while distinguishing it from altitude simulation setups used for cryogenic systems.

Cryo Main Engine Static Test Facility (CMEST)

The Cryo Main Engine Static Test Facility (CMEST) serves as a critical ground-testing infrastructure at the ISRO Propulsion Complex (IPRC) in Mahendragiri, Tamil Nadu, dedicated to evaluating cryogenic propulsion systems under sea-level conditions. Designed specifically for hot-fire static tests, it supports the qualification and performance validation of ISRO's indigenous cryogenic engines, including the CE-7.5 with a nominal thrust of 7.5 tonnes vacuum and the CE-20 delivering 20 tonnes vacuum thrust. These engines utilize liquid hydrogen (LH₂) and liquid oxygen (LOX) propellants, enabling high specific impulse for upper stages of launch vehicles. The facility's robust structural framework accommodates the extreme thermal and acoustic loads generated during engine firings, ensuring reliable data acquisition on thrust, chamber pressure, and propellant flow rates. Testing at CMEST encompasses full-sequence evaluations, including engine ignition, steady-state operation with throttling capabilities, and controlled shutdown procedures to simulate profiles. These sea-level static tests are pivotal for certifying the cryogenic stages of the GSLV Mk II and GSLV Mk III (now ) launch vehicles, verifying subsystem integration such as turbopumps and nozzle performance before flight integration. For example, the engine underwent successful flight acceptance hot testing for 25 seconds on March 14, 2025, confirming its readiness for the LVM3-M6 and demonstrating stable combustion across the rated thrust range of 186.36 kN. Such tests provide essential empirical data to refine engine design and mitigate risks in orbital insertion phases. In addition to core testing, CMEST incorporates advanced cryogenic handling systems with integrated safety interlocks to manage the hazards of sub-zero propellants, including automated abort mechanisms and remote monitoring for operator protection. While focused on simulations, these capabilities complement vacuum-condition evaluations at other IPRC facilities, collectively advancing ISRO's cryogenic technology maturity for heavier-lift missions. Ongoing enhancements ensure the facility can support extended-duration firings, aligning with evolving requirements for reusable and high-performance .

Semi-cryogenic Integrated Engine Test Facility (SIET)

The Semi-cryogenic Integrated Engine Test Facility (SIET) at the ISRO Propulsion Complex (IPRC) in Mahendragiri, Tamil Nadu, represents a pivotal advancement in India's space propulsion infrastructure, dedicated to the development and qualification of high-thrust semi-cryogenic engines. This state-of-the-art facility, comprising a 51-meter-tall test tower, was inaugurated by Prime Minister Narendra Modi, enabling comprehensive testing of engines utilizing liquid oxygen (LOX) and kerosene propellants. Designed to handle thrust levels up to 2,600 kN in the thrust chamber, SIET supports the SCE-200 engine, which delivers 2,000 kN (approximately 200 tonnes) of thrust, and includes an integrated stage testing bay for evaluating full engine-stage configurations. SIET's primary role involves conducting hot tests, including ignition trials and full-duration burns, to validate the performance, reliability, and integration of semi-cryogenic propulsion systems under operational conditions. These tests are essential for mitigating risks in engine development, such as and , particularly for kerosene-based systems that bridge the gap between traditional hypergolic and cryogenic engines in terms of and thrust density. The facility's capabilities are critical for prototyping engines destined for the (NGLV), aimed at enabling heavier payloads and reusable launch systems. A significant milestone at SIET occurred on March 28, 2025, when the first major hot test of the 's power head test article (PHTA) was successfully completed, achieving sustained 2,000 kN thrust and confirming the engine's potential for heavy-lift missions. This test validated key subsystems like the preburner and turbopumps, marking a breakthrough in ISRO's semi-cryogenic program and paving the way for subsequent integrated engine firings.

High Altitude Test Facility (HATF)

The High Altitude Test Facility (HATF) at the ISRO Propulsion Complex in Mahendragiri simulates conditions encountered by upper-stage engines during flight, enabling performance validation in a controlled low- environment. The core of the facility is a paired with a diffuser-ejector system, where ejectors maintain the necessary levels to replicate space-like conditions (as low as 50 mbar) and prevent issues like flow separation in engines with large ratios. This design supports short-duration hot firings of cryogenic engines, such as an 8-ton class tested in off-design configurations to assess feasibility for larger systems. Testing processes at the HATF focus on ignition, steady-state operation, and hot restarts under vacuum to gather data on plume expansion, thermal loads, and critical for mission success. For the cryogenic engine, which delivers approximately 20 tons of thrust for the upper stage, the facility has facilitated vacuum ignition trials with multi-element igniters, demonstrating reliable start-up at exit pressures as low as 50 mbar and validating restart-enabling systems for potential multiple firings in . These evaluations also examine interactions in upper-stage engine clusters, ensuring uniform thrust distribution and minimal plume impingement effects. The integration of cryogenic feed systems allows seamless delivery of and oxygen, supporting end-to-end qualification without interrupting the test sequence. Unique to the HATF is its role in bridging sea-level and full-space simulations, with the preventing reverse flows of unburnt propellants into the chamber during dynamic tests up to several seconds in duration. This capability has been instrumental in qualifying upper-stage components for missions requiring precise orbital maneuvers, while ongoing adaptations support emerging engines like the semi-cryogenic variants through preliminary performance checks.

Capabilities and Testing

Liquid and Hypergolic Propulsion Testing

The liquid and hypergolic propulsion testing at the ISRO Propulsion Complex (IPRC) centers on earth-storable propellants, particularly the hypergolic combination of nitrogen tetroxide (N₂O₄) as the oxidizer and (UDMH) or its hydrazine-augmented variant (UH25) as the fuel, which ignite spontaneously upon mixing to enable reliable engine starts. These propellants are selected for their long-term storability and operational simplicity in upper stages and propulsion systems, with testing focused on engines producing around 800 kN, such as the Vikas family used in ISRO's PSLV, GSLV, and vehicles. The protocols emphasize safety and precision, given the toxic and corrosive nature of these propellants, ensuring compliance with international standards for handling and disposal. Static firing tests form the core of the evaluation process, conducted in controlled environments to simulate flight conditions while measuring critical performance metrics. These sequences typically involve ignition, steady-state operation, and shutdown phases, with durations up to 240 seconds for campaigns, monitoring parameters such as (Isp ranging from ~280–310 seconds), chamber pressure (optimized around 50–60 ), and oxidizer-to-fuel mixture ratio (near 1.7–2.0 for balanced efficiency). Health monitoring integrates real-time sensors for vibration, temperature profiles, and flow rates to detect anomalies like injector erosion or instability, supporting refinements across over 100 test campaigns that have validated engine durability under repeated thermal cycling. Representative examples include throttleability demonstrations at 67% levels and restart capability tests, which confirm operational flexibility for mission-specific needs. These testing efforts have directly contributed to the qualification of Vikas engine variants, enabling their deployment in more than 50 PSLV launches where they power the second stage, delivering consistent thrust for precise payload insertion into low Earth orbits. Additionally, reliability data from hypergolic tests has informed the development of satellite apogee motors, such as the 440 N bipropellant , which has supported orbit-raising maneuvers in numerous ISRO missions by providing verifiable performance margins against degradation over extended storage periods. While storable propellant testing prioritizes ambient handling, IPRC's protocols occasionally interface with cryogenic extensions for hybrid stage validations.

Cryogenic and Semi-cryogenic Engine Qualification

The qualification process for cryogenic and semi-cryogenic engines at the ISRO Propulsion Complex (IPRC) in Mahendragiri focuses on verifying operational reliability, efficiency, and safety under simulated mission conditions, addressing the challenges of handling low-temperature propellants like and oxygen. These engines enable higher specific impulses for upper-stage propulsion, contrasting with the simpler storable hypergolic systems tested elsewhere at IPRC. The process encompasses component-level assessments, integrated hot firings, and anomaly investigations to meet stringent performance criteria before flight integration. Key engines undergoing qualification include the and cryogenic variants, which operate on a - combination to deliver specific impulses of approximately 450 seconds in , supporting efficient increments for geostationary launches. The , in particular, generates a nominal of 200 kN with a of 34.7, optimized for the upper stage. Meanwhile, the SCE-200 semi-cryogenic engine employs and refined to produce 2,000 kN of at , achieving a of around 320 seconds and bridging the gap between traditional cryogenic and hypergolic propulsion for higher payload capacities. Qualification protocols require each engine to undergo more than 10 hot tests, accumulating extensive burn durations to demonstrate and off-nominal operations, such as thrust variations and mixture ratio shifts. Endurance testing simulates mission profiles with burns ranging from 720 to 1,000 seconds, ensuring sustained performance without degradation; for instance, engines have completed individual hot tests exceeding 640 seconds while maintaining stable combustion. resolution is integral, as seen in the initial hot test of the SCE-200 power head, where an unanticipated turbine pressure spike at 2 seconds prompted termination but facilitated targeted refinements to the system for subsequent successful firings. Performance metrics, including thrust-to-weight ratios and stability, are rigorously measured to confirm scalability for missions like human-rated flights. These tests adhere to ISRO's qualification standards, equivalent to MIL-STD protocols, encompassing testing to withstand launch accelerations, to simulate extreme temperature swings from cryogenic storage to ignition, and to verify containment integrity. Such comprehensive evaluations ensure the engines' robustness against environmental stresses, with all components certified post-test for flight-worthiness.

Key Achievements and Developments

Major Tests and Contributions to Missions

The ISRO Propulsion Complex (IPRC) has conducted several landmark tests that have been pivotal for the qualification of systems used in India's launch vehicles. One significant achievement was the qualification testing of the cryogenic upper stage engine, which underwent rigorous developmental and acceptance tests at IPRC facilities in the early 2000s, enabling its integration into the (GSLV) series for operational missions. In 2015, IPRC performed the inaugural sea-level hot test of the high-thrust cryogenic engine, firing it for 800 seconds to validate performance parameters ahead of its use in the GSLV Mk III. These tests demonstrated the reliability of indigenous cryogenic technology under simulated flight conditions. A notable demonstration in propulsion innovation occurred in September 2022, when IPRC successfully tested a 30 kN motor using (HTPB-based) and oxidizer (), achieving sustained combustion for 15 seconds. This test highlighted the potential of systems for safer, more controllable thrust in future upper stages, marking a step toward greener alternatives. IPRC's testing expertise has directly contributed to over 100 successful stages across PSLV and GSLV missions, including the of Vikas engines for PSLV's second stage and cryogenic stages for GSLV, ensuring high reliability in 87 orbital launches as of November 2025. For the mission in 2023, IPRC played a key role by conducting acceptance tests on the cryogenic engine and Vikas engines integrated into the LVM3-M4 , supporting the precise required for lunar orbit insertion and soft landing. In the NISAR mission, IPRC facilitated the assembly, integration, and testing of the GSLV-F16's second stage, with stacking activities commencing in April 2025 prior to the July launch, enabling the successful deployment of the NASA-ISRO satellite into .

Recent Advancements (2024–2025)

In 2024, the ISRO Propulsion Complex (IPRC) marked significant progress with the inauguration of the Semi-cryogenic Integrated Engine Test Facility (SIET) on February 27 by Prime Minister , enabling high-thrust testing up to 2,600 kN for semi-cryogenic engines like the SCE-200. This facility supported initial subsystem tests for the SCE-200, including the successful first ignition trial of the pre-burner on May 2 at SIET, validating turbo-pump and ignition systems critical for future upgrades. Building on this in 2025, IPRC achieved a breakthrough with the first hot test of the SCE-200 Power Head Test Article (PHTA) on March 28, operating at 2,000 kN thrust to confirm propellant feed and combustion stability. Following the March test, IPRC conducted a short-duration hot test of the SCE-200 on April 24, 2025, further validating combustion stability. Concurrently, on March 27, the complex completed a 1,000-hour life test of the 300 mN Stationary Plasma Thruster at full 5.4 kW power, demonstrating reliability for electric propulsion in future satellites and deep-space missions. IPRC further contributed to the successful LVM3-M5/CMS-03 launch on November 2 by preparing and flagging off the enhanced C25 cryogenic upper stage on March 15, which included a post-injection reignition experiment to support multiple payload deployments. Looking ahead, IPRC's work aligns with reusable propulsion advancements, such as the January 17 demonstration of Vikas engine restart capability at the facility, essential for recoverable launch vehicles. Integration efforts include hot tests of the Service Module Propulsion System on July 3, qualifying its liquid apogee motors and reaction control thrusters for crewed orbital missions. These developments position IPRC to support 's ambitious 2026 schedule of seven missions by March, including uncrewed flights and enhanced heavy-lift operations.

Incidents and Safety

Reported Incidents

In July 2017, three employees of the ISRO Propulsion Complex (IPRC) in Mahendragiri, including two senior officials, were suspended for procedural lapses related to testing protocols. The action was taken to address deviations in standard operational procedures during engine testing activities at the facility. A separate incident occurred in September 2017 when an was reported in the vicinity outside the IPRC premises. Investigations confirmed the event was unrelated to IPRC operations or testing, with no damage to the facility or personnel. authorities filed complaints against media outlets for disseminating unverified reports that suggested an internal mishap. During the first hot test of the Power Head Test Article (PHTA) for the SCE-200 semi-cryogenic engine on July 1, 2023, at the Semi-cryogenic Integrated Engine Test Facility (SIET) in IPRC, the sequence was aborted at 2.0 seconds due to an unanticipated spike in turbine pressure followed by a loss of turbine speed. No injuries occurred, and the anomaly, which validated initial ignition performance up to 1.9 seconds, led to comprehensive design reviews and further investigations to refine the engine's system. Subsequent tests addressed these issues successfully, with key verifications achieved in 2024 and 2025. These events represent the primary reported incidents at IPRC, underscoring an overall low rate of major occurrences at the complex, with no further incidents reported through 2025. Post-incident responses included procedural enhancements, as outlined in the facility's protocols.

Safety Protocols and Responses

The ISRO Propulsion Complex (IPRC) implements multi-layer protocols encompassing remote monitoring systems, automated shutdown mechanisms, and specialized mitigation strategies for cryogenic hazards such as and leaks, ensuring operational integrity during high-risk tests. These protocols are supported by annual drills focusing on response coordination and containment to maintain a zero-defect environment. Additionally, systems track propellant emissions to minimize ecological impact in compliance with ISRO's internal environmental standards. IPRC adheres to ISRO's comprehensive safety standards for handling hazardous materials in space-related activities, including chemical risk assessments. Post-incident responses have driven enhancements, such as the 2017 procedural lapses that prompted internal audits and the implementation of stricter access controls via biometric systems to bolster facility security. Following the semi-cryogenic engine test anomaly involving the turbine, IPRC initiated redesign efforts, including ignition-resistant coatings and upgraded simulation tools.

References

  1. [1]
    About IPRC | Department of Space, Government of India.
    ISRO PROPULSION COMPLEX (IPRC), formerly known as Liquid Propulsion Systems Centre, Mahendragiri (LPSC-M), is located near Kanniyakumari at Mahendragiri ...
  2. [2]
    ISRO Propulsion Complex (IPRC)
    Jan 24, 2025 · IPRC is responsible for the supply of Storable Liquid Propellants for ISRO's launch vehicles and satellite programmes. IPRC delivers quality ...
  3. [3]
    ISRO Propulsion Complex (IPRC), Mahendragiri
    The IPRC is responsible for the supply of storable liquid propellants for ISRO's launch vehicles and satellite programmes. The IPRC delivers quality products to ...
  4. [4]
    ISRO conducts successful hot tests of Gaganyaan Service Module ...
    Jul 9, 2025 · ISRO successfully conducted two hot tests of the Gaganyaan Service Module Propulsion System (SMPS) on July 03, 2025 at ISRO Propulsion Complex (IPRC), ...
  5. [5]
    ISRO successfully conducted a short duration hot test of ...
    Apr 26, 2025 · A short duration hot test of the Semicryogenic Engine was successfully conducted at the test facility in ISRO Propulsion Complex (IPRC), Mahendragiri on April ...
  6. [6]
    ISRO achieves major breakthrough in Semicryogenic Engine ...
    Mar 29, 2025 · The complex Semicryogenic Integrated Engine Test facility (SIET) was established at ISRO Propulsion Research Complex (IPRC), Mahendragiri for ...
  7. [7]
    Russian route - Frontline - The Hindu
    Jan 22, 2014 · Once import of Russian technology became possible, indigenous development, which, since the 1970s ... Mahendragiri (southern Tamil Nadu) liquid ...
  8. [8]
    Vikas Engine - Gokulam Seek IAS Academy
    Jan 22, 2025 · Hypergolic liquid-fuel rocket engines developed by ISRO. 1st developed in the 1970s. Designed by ISRO's Liquid Propulsion Systems Centre (LPSC).
  9. [9]
    ISRO Propulsion Complex (IPRC) - VSSC
    Oct 31, 2021 · IPRC ISRO Propulsion Complex (IPRC), Mahendragiri is equipped with state-of-the-art- facilities necessary for realising the cutting edge technology products.
  10. [10]
    Museum Visit Request - IPRC
    Jan 23, 2025 · IPRC Museum Visit. For IPRC Museum Visit, Please Contact : 04637-281211 / 281230. Website Policy | Right to Information | Sitemap | Help ...
  11. [11]
    None
    ### Summary of IPRC Content
  12. [12]
    Our Director | Department of Space, Government of India.
    Shri. J. Asir Packiaraj, 'Distinguished Scientist', is the Director of ISRO Propulsion Complex (IPRC) Mahendragiri, Tamil Nadu. He is a graduate in Mechanical ...
  13. [13]
    [PDF] government of india
    Aug 10, 2023 · MON-3 plant is operated & managed by Vikram Sarabhai Space Centre (VSSC) but located at ISRO Propulsion Complex (IPRC). The ISRO propulsion ...
  14. [14]
    Indian Space Research Organisation - ISRO
    Jan 14, 2025 · Dr. Narayanan was a member of ISRO's 12th Five-Year Plan Drafting Group and contributed to finalizing the propulsion system development during ...Missing: history | Show results with:history
  15. [15]
    [PDF] भारत सरकार government of india अनुदानों की यौरेवार मांग ... - ISRO
    provided for in the Budget Estimates 2025-2026. A36. वष 2023-2024 के ... ISRO PROPULSION COMPLEX (IPRC). 6,24,973. 6,60,000. 6,30,000 ęĸćċ. 55.00.01.
  16. [16]
    Liquid Propulsion Systems in ISRO - Evolution and Perspective | Journal of Aerospace Sciences and Technologies
    ### Summary of LPSC and Mahendragiri Unit History and Development
  17. [17]
    [PDF] Indigenous Cryogenic Technology:
    The indigenous cryogenic engine was developed at the Liquid. Propulsion System Centre (LPSC), Mahendragiri, near Nagercoil in. Tamil Nadu. During the period ...
  18. [18]
    Vikas Engine - GKToday
    The first flight using a Vikas Engine took place in 1980 on the Rohini Satellite Launch Vehicle (RSLV) test series, and by the late 1980s, it was integrated ...
  19. [19]
    Isro's Mahendragiri centre elevated, gets more powers - Times of India
    Feb 1, 2014 · The move would now help the complex to get autonomous power and would function as a separate department of Isro. The Mahendragiri centre, which ...Missing: IPRC | Show results with:IPRC
  20. [20]
    Technical 'Anomaly' Puts Off ISRO's Key CE-20 Test
    May 31, 2015 · On April 28 this year, ISRO had created history by burning the CE-20 for 635 seconds in a ground-based test- the full duration it will need to ...
  21. [21]
    Cryogenic success - Frontline - The Hindu
    Jan 22, 2014 · In a major breakthrough that promises to make India self-reliant in space technology, an indigenised cryogenic engine powers the Geosynchronous ...Missing: reforms | Show results with:reforms
  22. [22]
    Successful completion of human rated Vikas engine test campaign ...
    Apr 6, 2023 · ISRO could complete the human rated L110-G Vikas engine qualification within a short span of three years. The test was witnessed by Shri S ...Missing: history Viking
  23. [23]
    ISRO Sets New Benchmark with Successful Semi-Cryogenic Engine ...
    Jun 7, 2025 · Principal Test Stand (PST):. The oldest facility, designed for testing the Vikas engine and other hypergolic engines. Importance of the Facility ...
  24. [24]
    ISRO successfully conducted the flight acceptance hot test of CE20 ...
    Mar 17, 2025 · On March 14, 2025, ISRO successfully conducted the flight acceptance hot testing of the cryogenic engine identified for the sixth operational mission of LVM3 ...
  25. [25]
    ISRO tests Cryogenic Engine (CE-20) for GSLV Mk-III
    Sep 20, 2023 · The CE-20 engine has a thrust of 186.36 kN and a specific impulse of 442 seconds. Its hot test showed steady operation and normal subsystem ...
  26. [26]
    Hon'ble Prime Minister of India Shri Narendra Modi visited VSSC
    Feb 29, 2024 · Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram of ISRO played host to a landmark event on February 27, 2024, when Prime Minister of India Shri ...
  27. [27]
    Successful ignition test on Semi Cryogenic Pre-Burner ... - ISRO
    May 6, 2024 · The first ignition trial was conducted successfully on May 2, 2024, at semi cryo integrated engine test facility (SIET) at IPRC, Mahendragiri.Missing: Static LH2 storage date
  28. [28]
    Isro achieves major breakthrough in semicryogenic engine for ...
    Mar 29, 2025 · The complex Semicryogenic Integrated Engine Test facility (SIET) was established at its Propulsion Research Complex (IPRC), Mahendragiri for ...
  29. [29]
    ISRO Marks Major Progress in Semi-Cryogenic Engine Development
    Mar 29, 2025 · ISRO has made significant progress in developing a semi-cryogenic engine, successfully conducting a hot test of the Engine Power Head Test Article.
  30. [30]
    ISRO's second short hot test of semicryogenic engine a success
    Apr 27, 2025 · ISRO has successfully conducted a short duration hot test of the semicryogenic engine at its facility in the ISRO Propulsion Complex (IPRC), Mahendragiri.<|control11|><|separator|>
  31. [31]
    [PDF] CFD Analysis of High Altitude Test Facility for Off-Design Operation
    A HAT facility typically consists of a vacuum chamber and a diffuser-ejector system. The diffuser- ejector system is designed to maintain the necessary low.Missing: km | Show results with:km
  32. [32]
    Vacuum ignition trial of Cryogenic engine with Multi-element ... - ISRO
    Feb 10, 2025 · During this test, the ignition of the engine Thrust Chamber was carried out with a multi-element igniter in vacuum, under the tank pressure ...Missing: specifications operational 2010 30 km steam ejectors<|control11|><|separator|>
  33. [33]
    Why Is ISRO's CE20 Cryogenic Engine Ignition Test Significant?
    Feb 12, 2025 · High exit pressure of 50 mbar. Conducted tests at a High Altitude Test Facility (HAT) to validate performance. Outcome: The test was ...<|control11|><|separator|>
  34. [34]
    Geosynchronous Satellite Launch Vehicle Mark II - ISRO
    Sep 20, 2023 · Technical Specification ; Third Stage: CUS · : LOX + LH2. Nominal Thrust (Max), : 75 kN ; Second Stage: GS2 · Engine, : Vikas · : UH25 + N2O4.
  35. [35]
    FAQ - LPSC
    The PS2 stage is powered by a Vikas engine with 800kN thrust and stage propellant loading of 40 tons. The fourth stage is powered by two PS4 engines delivering ...Missing: specifications Isp
  36. [36]
    [PDF] Major Activities of ISRO
    ISRO's activities include satellite building, advanced propulsion, human space flights, research, and satellite data utilization, covering space infrastructure ...
  37. [37]
    Successful Qualification of High Thrust Vikas Engine - ISRO
    May 1, 2023 · A high thrust version of the Vikas Engine was successfully qualified through a ground test for a duration of 195 seconds at ISRO Propulsion Complex (IPRC), ...Missing: hypergolic | Show results with:hypergolic
  38. [38]
    Successful test of Throttleable Vikas Engine for 67% Thrust level
    May 1, 2023 · The first Throttling demonstration hot test of the Vikas engine was successfully accomplished on January 30, 2023 for a targeted 67% thrust level throttling ...
  39. [39]
    [PDF] publication(26).pdf - ISRO
    The 440 Newton liquid propulsion motor is used for orbit raising. The satellite uses passive thermal control system. The satellite has two antennas that are ...
  40. [40]
    CE20 E13 Engine Hot Test for 22t Thrust Qualification - ISRO
    Oct 11, 2023 · The engine was already qualified to operate at a thrust level of 19 tonnes and performed successfully in 6 successive LVM3 missions, including ...
  41. [41]
    Successful CE20 uprated Engine Hot Test with 21.8 T vacuum thrust
    Nov 9, 2022 · During this test the engine operated with ~20 t thrust level for the first 40s, then the thrust level was increased to 21.8t by moving the ...<|separator|>
  42. [42]
    Successful third Hot Test of Semi-Cryogenic Engine
    Jun 1, 2025 · May 31, 2025. ISRO commenced a series of performance evaluation tests in March 2025 of the Semicryogenic engine Power Head Test Article ...
  43. [43]
    First hot test of the Semi-cryogenic engine conducted at IPRC ... - ISRO
    Jul 2, 2023 · The test was conducted towards developing a 2000 kN thrust semi-cryogenic engine to power the booster stages of future launch vehicles.
  44. [44]
    CE20 E13 Engine Hot Test for the Gaganyaan & 22t Thrust ... - ISRO
    Sep 25, 2023 · During this test, the CE20 engine operated at the coveted 22-tonne thrust level for a duration of 670 seconds. Both the engine and the testing ...Missing: first 2015
  45. [45]
    ISRO completes final test for Gaganyaan rocket engine that can ...
    Feb 21, 2024 · "All the ground qualification tests of the CE20 engine for the Gaganyaan programme have been successfully completed," said the national space ...
  46. [46]
    [PDF] Technology Transfer - ISRO
    testing as per ISRO qualification standards and can be qualified for the space use only after successful completion of the testing. ISRO offers to transfer.
  47. [47]
    GSLV-Mk III project on course as India test-fires indigenous cryo ...
    Jul 20, 2015 · Isro on Monday confirmed that the test was conducted at the Isro Propulsion Complex at Mahendragiri in southern Tamil Nadu for 800 seconds, ...
  48. [48]
    30 kN Hybrid Motor Successfully Tested at IPRC on 20/09/2022 - ISRO
    Sep 14, 2023 · Today's test of a flight equivalent 30 kN hybrid motor demonstrated ignition and sustained combustion for the intended duration of 15 seconds.Missing: demonstration | Show results with:demonstration
  49. [49]
    The making of Chandrayaan-3: collaborative effort under the 'ISRO ...
    Sep 18, 2023 · In particular, LPSC contributes rocket engines and propellants, and IPRC conducts engine testing. SDSC-SHAR, Sriharikota, manufactures solid ...
  50. [50]
    GSLV Second Stage (GS2) flagged off to Sriharikota for GSLV-F16
    Apr 28, 2025 · The Second Stage (GS2) of ISRO's GSLV launch vehicle was flagged off by Dr. V. Narayanan, Secretary, DOS/ Chairman, ISRO, on April 24, 2025.Missing: stacking | Show results with:stacking
  51. [51]
    PM visits Vikram Sarabhai Space Center (VSSC) in ... - PIB
    Feb 27, 2024 · The Prime Minister, Shri Narendra Modi visited Vikram Sarabhai Space Center (VSSC) at Thiruvananthapuram, Kerala and inaugurated three important ...Missing: SIET | Show results with:SIET
  52. [52]
    ISRO successfully completes 1000hrs Life Test of Stationary Plasma ...
    Mar 29, 2025 · On March 27, 2025, ISRO successfully completed the life test of 1000hrs on the 300mN Stationary Plasma Thruster, that is developed for induction ...
  53. [53]
    Cryogenic Upper Stage (C25) for LVM3 flagged off to Sriharikota
    Mar 17, 2025 · ISRO flagged off the Cryogenic Upper Stage (C25) of ISRO's LVM3 launch vehicle on March 15, 2025, from the ISRO Propulsion Complex (IPRC), Mahendragiri, to the ...
  54. [54]
    ISRO scientists perform vital experiment in LVM3-M05 mission's ...
    Nov 2, 2025 · ISRO scientists have carried out a new experiment on the indigenously developed C25 cryogenic stage of the LVM3-M5 rocket which successfully ...
  55. [55]
    ISRO demonstrates restart of Vikas engine - Reddit
    Jan 17, 2025 · Vikas is a low Isp, high thrust booster class engine nothing more. ... Specific impulse (as explained by Scott Manley on YouTube). Internet ...ISRO's 'Vikas' rocket engine that powers the PSLV, GSLV and LVM3 ...Russia offers India semi-cryogenic engine technology : r/ISRO - RedditMore results from www.reddit.com
  56. [56]
    https://m.economictimes.com/news/science/isro-scientists-perform-vital-experiment-in-lvm3-m05-missions-cryogenic-stage/articleshow/125036745.cms
  57. [57]
    Three ISRO officials suspended for lapses - The New Indian Express
    Jul 15, 2017 · Three employees, including two senior officials of ISRO Propulsion Complex, Mahendragiri in Tirunelveli have come under scanner for alleged procedural lapses.<|separator|>
  58. [58]
    'Explosion at IPRC': TV reporters may face legal action - The Hindu
    Sep 25, 2017 · 'Explosion at IPRC': TV reporters may face legal action. They presented 'story' on 'mysterious explosion' at Mahendragiri complex. Published - ...
  59. [59]
    Case against journalists for carrying false reports about IPRC
    Sep 27, 2017 · Case against journalists for carrying false reports about IPRC. Pertains to claims of a mysterious explosion on the premises. Updated - ...
  60. [60]
    ISRO files police complaint against rumours about smoke on its ...
    Sep 26, 2017 · Anti-Naxal team and CISF took up the investigation after reports of smoke emanating on the campus in Mahendragiri of Tirunelveli district on ...Missing: IPRC | Show results with:IPRC
  61. [61]
    List of spaceflight-related accidents and incidents - Wikipedia
    This article lists verifiable spaceflight-related accidents and incidents resulting in human death or serious injury. These include incidents during flight ...
  62. [62]
    ISRO Pollution Monitoring At SDSC - Resustainability
    Dec 9, 2024 · Environmental Monitoring and Analytical Services during ISRO Satellite Launches. • Focused monitoring N₂O₄ and UDMH used as rocket propellants.Missing: Propulsion Complex
  63. [63]
    Codes & Guides | AERB - Atomic Energy Regulatory Board
    AERB issues Draft Safety Codes / Safety Standards to solicit public comments and their participation in developing Safety Requirements. Please Click here ...
  64. [64]
    PO DETAILS - ISRO Propulsion Complex
    2025G033610101, DSO FOR SAFETY MONITORING, ELMACK ENGG. SERVICES, 142750.0000, 23/10/2025 ... Rate Contract for Repairing of Office Furniture at IPRC, ...
  65. [65]
    Isro semi-cryo engine test terminated mid-way - The Times of India
    Jul 3, 2023 · This story is from July 3, 2023. Isro semi-cryo engine test terminated mid-way ... semi-cryogenic engine to power the booster stages of ...
  66. [66]
    [PDF] Respond BASKET - 2023 - ISRO
    Jan 31, 2024 · RESPOND Basekt-2023 is an invitation extended with great enthusiasm to the academic community to participate by submitting proposals and ...