ISRO’s Semi-Cryogenic Engine Test

ISRO’s Semi-Cryogenic Engine Test

Sub :Sci

Sec: Space

Introduction

• ISRO successfully conducted the hot test on a semi-cryogenic engine (SE2000), marking a crucial step toward finalizing the cryogenic stage for future heavy-lift space missions.
• The test, known as the Power Head Test Article (PHTA), is the first hardware test in the development of semi-cryo engines.

Power Head Test Article (PHTA)

• The PHTA, without the thrust chamber, has been successfully realized.
• It is approximately 3 meters in height.
• A crucial precursor test to validate the integrated performance of key subsystems, including:
  • Gas generator
  • Turbo pumps
  • Pre-burner
  • Control components
• The test involved hot-firing for a brief duration of 4.5 seconds.

Previous Attempts

• A July 2023 test attempt at ISRO’s Mahendragiri facility was aborted due to a technical glitch.
• Since then, the ISRO team has worked on developing the semi-cryogenic engine with 2,000 kN thrust.

Propulsion Systems in ISRO

• Propulsion systems provide the muscle power for a rocket’s liftoff and journey into space.
• Selection of propellant systems depends on:
  • Thrust required
  • Reusability
  • Cost-effectiveness
  • Core competency
• ISRO has been using environment-friendly propellants such as:
  • Liquid Oxygen (LOX)
  • Liquid Hydrogen (LH2)
  • LOX-Kerosene-based propulsion systems

Comparison: Cryogenic vs. Semi-Cryogenic Engines

• Cryogenic Engines:
  • Uses Liquid Oxygen (LOX) and Liquid Hydrogen (LH2).
  • Liquid Hydrogen storage is challenging (requires -253°C and is highly inflammable).
• Semi-Cryogenic Engines:
  • Uses Liquid Oxygen (LOX) and Kerosene.
  • Advantages:
    • Readily storable kerosene.
    • High-density impulse compared to cryogenic.
    • Less toxic and cost-effective.

LVM3 and Future Developments

• ISRO is working on Launch Vehicle Mk III (LVM3) with the C32 cryogenic upper stage.
• Advantages of C32 over C25:
  • Carries more propellant, increasing space mission life.
  • Enhances payload capacity by 25%.
• Future goals:
  • Increase launch capacity from 4 tonnes to 5.1 tonnes at Geosynchronous Transfer Orbit without raising costs.
  • Develop a LOX-kerosene propulsion system powered by a 2,000-tonne thrust engine.

Development of Next Generation Launch Vehicle (NGLV)

• NGLV will be used for Gaganyaan missions.
• It is a new-generation human-rated launch vehicle.
• Features:
  • High payload capacity and reusability.
  • Reusable first stage, offering 30 tons to Low Earth Orbit.
• Structure:
  • First and second stages will use LOX engines.
  • Upper stage will be a cryogenic stage.
• The design is complete, and ISRO has moved to the development phase.

Advancements in Reusability

• ISRO is developing technologies for recovering and reusing launch vehicles.
• Recent success in recovering the first stage of NGLV.

Future Propulsion Systems

• A specialized ISRO team is studying advanced propulsion systems.
• Proposed new system:
  • Normal aircraft-like takeoff.
  • Switches to cryogenic engine mid-flight.
  • Covers thousands of kilometers across continents in just hours.