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Aerothermal Design of Space Transportation Systems 1
Vorlesung
Aerothermal Design of Space Transportation Systems
Dr.-Ing. Ali Gülhan [email protected]
DLR Köln
Ascent configurations Hypersonic vehicles Re-entry vehicles (lifting body)
Aeroassited orbital transfer vehicles (capsules)
Mach number: 0-7 Mach number: 0-12 Mach number: 28-0 Mach number: 35-0
Complex base flow interactions
Inlet unstart Strong non-equilibrium effects
Stron non-equilibrium effects
Unsteady flow phenomena
Shock wave boundary layer interaction on the inlet ramps
Shock wave boundary layer interaction on control surfaces
Radiative heating
Flow separation inside the nozzle and in the base
Effect of the combustion instability on the complete aerodynamics
Boundary layer transition and leading to strong aerothermal heating
Roughness induced transition and leading to strong aerothermal heating
SERN nozzle flow Boundary layer contamination due to ablation products
Flow Induced Problems of Space Transportation Vehicles
Aerothermal Design of Space Transportation Systems 2
Flow Induced Problems of Ascent Configurations
Instationary flow separation inside the nozzle at low altitudes and booster separation lead to strong side loads and buffeting effects [1,2]
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Flow Induced Problems of Ascent Configurations
At high altitudes the nozzle is underexpanded and the plume flow expansion leads to flow separation in the base and aerothermal loads [3]
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- Inlet flow and inlet unstart problem, - Shock/Shock and Schock/Boundary Layer Interaction, shock trains - Influence of the combustion on nozzle flow, i.e netto thrust
Flow Induced Problems of Hypersonic Vehicles
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- Aerthermal loads on the inlet ramp due to boundary layer transition - Influence of the combustion on nozzle flow, i.e netto thrust
Flow Induced Problems of Hypersonic Vehicles
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Flow Induced Problems of Re-entry Vehicles (Lifting Body)
- Gap and step heating - Severe aerothermal heating due to the boundary layer transition during re-entry
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- Aerothermal heating due to recombination reactions - Shock/Shock and Schock/Boundary Layer Interaction
Flow Induced Problems of Re-entry Vehicles (Lifting Body)
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- Strong non-equilibrium effects on aerothermal heating - Radiative heating and ist coupling with convective heating - Roughness induced transition with enhanced aerothermal heating - Dynamic stability problems of the capsule in particular in transonic regime
Flow Induced Problems of Re-entry Vehicles (Capsules)
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ESA MarsExpress Mission
Start 2. June 2003
Launcher Soyuz/Fregat
Total mass 1200 kg
Propellant mass 428 kg
Orbiter mass 113 kg
Lander mass 60
Arrival at Mars 25. December’03
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Critical Flight Phases Launch, Entry, Descent and Landing
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Flight Experiment
Numerics Ground Testing Aerothermal Design of Space Transportation Systems 12
Content /1
• Flow induced problems of space vehicles ⇒ Space transportation missions and vehicles ⇒ Atmospheric properties of different atmospheres ⇒ Flow regimes
• Flow regimes ⇒ Flow regimes depending on the Mach number, Reynolds number and Knudsen number
• Methods of preliminary spacecraft design ⇒ Prandtl-Meyer Expansion und Isentropic Compression ⇒ Newtonian Flow ⇒ Tangent Wedge Method ⇒ Tangent Cone Method ⇒ Shock Expansion Method ⇒ Method of Characteristics
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Content /2
• Effects of viscous hypersonic flows on spacecraft design ⇒Boundary Layer Flow ⇒Main Properties of Viscous Flow ⇒Strong and weak viscous interaction
• Effects of boundary layer transition on spacecraft design ⇒Methods to Predict Boundary Layer Transition ⇒Aerothermodynamic Effects caused by Boundary Layer Transition ⇒Methods to mitigate boundary layer transition effects
• Effects of strong interaction phenomena on spacecraft design ⇒Flow Separation ⇒Shock-Shock Interaction ⇒Shock-Boundary-Layer Interaction ⇒Examples from Space Transportation Mission
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Content /3 • High Enthalpy Flow
⇒Dissociation and Recombination Effects ⇒Thermal und Chemical Non-equilibrium ⇒Surface Catalytic Recombination
• Thermal Protection Systems ⇒ CMC materials ⇒ Ablation materials
• Fluid-Structure-Interaction during hypersonic flight
⇒Thermal interaction ⇒Structural interaction
• Spectroscopic methods to characterize high enthalpy flows
⇒ Flow characterization ⇒ Material characterization
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Content /4
• Aerodynamic stability of spacecraft ⇒Basics of aerodynamic stability ⇒Methods to determine aerdynamic stability
• Health monitoring of spacecraft
⇒Instrumentation ⇒Thermalmanagement ⇒Plasma flow control
• Simulation Tools ⇒ Numerical tools ⇒ Ground testing facilities
(including visit of facilities at DLR Cologne) • Design and Performing Hypersonic Flight Experiments
⇒ Design of hypersonic flight experiments ⇒ Critical aspects of hypersonic flight experiments ⇒ Post flight analysis
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