The BrahMos missile employs a two-stage propulsion system designed for high-speed, long-range supersonic cruise performance. The propulsion configuration combines a solid propellant booster for initial launch acceleration with a liquid-fueled ramjet engine that sustains flight at supersonic speeds. This advanced propulsion architecture enables the missile to maintain speeds of approximately Mach 2.8–3.0 during its operational flight.
Key Details:
Category: Two-Stage Missile Propulsion System
Propulsion Configuration:
Stage 1: Solid Propellant Booster
Stage 2: Liquid-Fueled Ramjet Sustainer
Stage 1 – Solid Propellant Booster:
Description: A powerful solid composite propellant motor ignites
immediately after launch to generate high thrust. This booster rapidly
accelerates the missile from rest to supersonic speeds before separating
once the required velocity is achieved.
Function: Provides the initial thrust required to launch and
accelerate the missile to near operational cruising speed.
Stage 2 – Liquid Fuel Ramjet Sustainer:
Description: After booster separation, a liquid-fueled ramjet
engine takes over propulsion. The ramjet uses atmospheric oxygen
combined with a high-energy liquid fuel to sustain combustion while
maintaining supersonic flight.
Fuel Type: High-density kerosene-based fuel similar to modified
aviation turbine fuel (ATF) or Russian T-6 class fuels designed for
high-speed propulsion.
Function: Enables sustained supersonic cruise at speeds
approximately between Mach 2.8 and Mach 3.0 during the main phase
of flight.
Operational Characteristics:
Note: The exact chemical compositions and engineering details of the propulsion system remain proprietary and confidential due to their strategic military significance.
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