P M V Subbarao Professor Mechanical Engineering Department

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Presentation transcript:

P M V Subbarao Professor Mechanical Engineering Department Analysis of Missiles P M V Subbarao Professor Mechanical Engineering Department Simple Propulsion Systems but not for Humans!!!

Hypersonic Flyers : Comprehensive Mechanism of Intake Air Control = 1 + g - ( ) 2 x s i b æ è ç ö ø ÷ M y = n s i b - q ( )

Oblique Shock Wave Angle Chart max curve Mx=5.0 Mx=3.0 Mx=1.5 Mx=4.0 Mx=2.5 Mx=2.0

Performance of An Adiabatic Oblique Shock y x = 1 + 2 g ( ) M n - T y x = 1 + 2 g ( ) M n - é ë ê ù û ú But Pressure Recovery Factor or Total Pressure Ratio for the oblique shock :

Performance of An Adiabatic Oblique Shock Across a Shock Available Resource Pressure Recovery Factor or Total Pressure Ratio for the oblique shock :

Performances of NS & OS The total pressure recovery of a normal shock rapidly deteriorates beyond Mach ~ 1.6. 90% total pressure recovery is achieved at 1.6.

Simplest Reversible Inlet of A Missiles Oblique Shock Normal Shock A single compression ram inlet involves one oblique shock and one normal shock.

Inlet with Multiple External Compressions A double compression ram inlet involves two oblique shocks and one normal shock.

Multiple External compressions Inlets

Performance Enhancement of External Compressions to Inlet

Special Designs of Center Bodies If there are multiple shocks: Mx My1 My2 My3 q

The Ancient Flyers : Ramjets (Asthras) Only three operating components: A central Body intake (diffuser) burner (combustion chamber); nozzle

Ramjets - Basic Operating Features External shock decelerate ambient air entering the flyer. This Air is further decelerated in intake (diffuser). The pressure rises due to ram effect. Known as ram pressure and significant at supersonic speeds. A ramjet therefore needs no machines or engine to increase the pressure. Simplifies the design and reducing the cost. Greatest disadvantage is that it has to be accelerated up to very high speed before it produces any useful thrust. Also complicated supersonic intake required to avoid shock losses.

The Asthra : Modern Models

Frictionless Flow through Constant area Pipe with Heat Transfer exit inlet Momentum equation gives Integrating from inlet to exit: