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130 MM Boost-Sustain Motor
A 130 MM Boost-Sustain Motor is a solid rocket propulsion unit designed to provide a dual-thrust performance profile within a single motor system. Typically measuring around 130 mm in diameter, this type of motor delivers a high initial thrust phase to rapidly accelerate a projectile, followed by a lower, sustained thrust phase that maintains velocity during flight.
Key Details:
Category: Solid Rocket / Missile Propulsion System
Motor Diameter:
130 mm Boost-Sustain Motor: Designed for missile or rocket
systems that require rapid launch acceleration followed by sustained
propulsion during flight.
Description:
Chemical Composition: These motors commonly utilize composite
solid propellants. Typical formulations include ammonium perchlorate
as the oxidizer, atomized aluminum powder as the metallic fuel, and
polymer binders such as hydroxyl-terminated polybutadiene (HTPB) or
polybutadiene acrylonitrile (PBAN). Catalysts or additives such as
iron oxide may be incorporated to control burn rate and improve
combustion characteristics.
Design: The boost-sustain configuration refers to the internal
grain geometry of the solid propellant. The grain is engineered to
burn quickly at ignition to generate a strong initial boost phase,
followed by a slower burn rate that sustains thrust during flight.
Component Structure: The motor typically includes a durable
casing, nozzle assembly, ignition system, and a solid propellant
grain. During combustion, exhaust gases are expelled through the
nozzle to produce thrust.
Common Uses:
- Missile Propulsion: Used in short-to-medium range tactical missile systems requiring rapid acceleration and sustained flight.
- Ramjet Acceleration: Serves as a booster stage to accelerate projectiles to speeds required for ramjet engines to operate.
- Specialized Launch Systems: Integrated into launch platforms where controlled thrust and efficient propulsion are required.
Operational Features:
Dual-thrust boost-sustain propulsion profile, high-energy composite
propellant, efficient burn characteristics, and reliable ignition for
consistent performance during launch and sustained flight phases.
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