aerothermodynamic analysis of innovative …
TRANSCRIPT
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AEROTHERMODYNAMIC ANALYSIS OF INNOVATIVE HYPERSONIC DEPLOYABLE
REENTRY CAPSULES
Raffaele SavinoUniversity of Naples Federico II
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Objectives
Show the main capabilities of deployable aero-brakes for Earth re-entry capsules
Perform aerothermodynamic and mission analyses of such re-entry systems
Assess some feasible missions offered by the system
Study and design technological demonstrators for the experimental verification of the system effectiveness and functionality along different sub-orbital flight profiles
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Introduction (1)
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Thermal and mechanical loads
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Orbital missions
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Sub-orbital missions
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TPS materials
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Re-entry from LEO
• CubeSats
• Contrast the phenomenon of Space debris• Match the 25 years requirement for orbital decay• Enable orbit insertion at larger altitudes• Possibility to recover payloads and data
§ Reduce costs reusing hardware and subsystems§ Perform post-flight inspections and experimentations
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Re-entry from LEO
• De-orbit trajectories
Standard CubeSat CubeSat with aerobraking system
• Possibility to increase the orbit altitude for orbital decay• Significant reduction of the orbital decay lifetime
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Re-entry from LEO• Air-launchable system
• The orbital injection can be performed at relatively low altitude to reduce size, mass and cost of optical equipment, optimize the spatial resolution on the ground
• Many kind of orbits can be selected for efficient Earth observations or for other objectives, depending on the specific mission requirement, due to the flexibility offered by air launch
• The deployable aerobrake can allow the capsule to perform efficient manoeuvres in a relatively short time, with low risks and avoiding any propulsive boost
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Re-entry from LEO
• Aerodynamic control of de-orbit trajectories• The reference surface modulation can be exploited to cope
with the off-nominal conditions along the de-orbit trajectory (like, in this case, the air density disturbances) to correctly target the capsule towards the selected landing site
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Re-entry from LEO
• De-orbit and re-entry trajectories
H = 76.4 km, M∞ = 20.7
H = 63.5 km, M∞ = 11.0
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Re-entry from LEO
• CFD and DSMC Aerothermodynamic analyses
H [km] M∞ [-] Re∞ [-]
76.4 20.7 14165
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Re-entry from LEO
• Aerodynamic stability
CG=A CG=B CG=C CG=D CG=E
dCmz/dα [deg-1] -4.5∙10-3 -3.3∙10-3 -2.1∙10-3 -1.0∙10-2 3.7∙10-3
Nominal re-entry attitude
H [km] M∞ [-] Re∞ [-]
50.0 3.30 65096
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Technology demonstrator
• Technology demonstrator for Maxus rocket (IRENE, ALI)
• Compatibility with Maxus interstage• Total mass less than or equal to 15 kg• Ballistic coefficient lower than 20 kg/m2• Automatic system for TPS deployment• TPS able to withstand heat fluxes in the order of 300-350 kW/m2
• Structure able to withstand mechanical loads in the launch phase & aerodynamic loads in the atmospheric re-entry phase
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Technology demonstrator
• Technological demonstration mission
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Technology demonstrator
• Suborbital re-entry trajectories
H = 47.0 km, M∞ = 9.00 H = 38.0 km, M∞ = 6.50
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Technology demonstrator
• CFD Aerothermodynamic analyses
Pressure [Pa]
Temperature [K]
• Air can be considered in chemical equilibrium, due to the relatively low energy profile
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Technology demonstrator
• Technology demonstration mission for Rexus
• Compatibility with Rexus payload fairing• Total mass around 5 kg• Automatic system for TPS deployment• Structure able to withstand mechanical loads in the
launch phase and aerodynamic loads during the atmospheric re-entry phase
• Launch from Kiruna within the Rexus fairing• Ejection from the rocket fairing after the nosecone fairing
ejection and before the rocket de-spinning• Aerobrake deployment during descending parabola• Telemetry retrieval of critical data• Landing and recovery
• Main requirements
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Technology demonstrator
• Suborbital re-entry trajectories
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Technology demonstrator
• CFD Aerodynamic analysesH [km] M∞ [-] Re∞ [-]
45.0 1.38 47647
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Technology demonstrator
• CFD Aerodynamic analyses
• Frequency: 14 Hz
T0 T0+0.02T0+0.04
T0+0.07p [Pa] CL [-] CD [-] CM [-]≈ 80 ≈ 0.020 ≈ 0.015 ≈ 0.040
• Amplitude:
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Wind tunnel model
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Conclusions
Numerical models show the possibility to study different scenarios for orbital re-entry
and for suborbital demonstrators
A new method for the aerodynamic control of a variable geometry umbrella-like structure
has been proposed
Evaluation of the aerothermodynamic conditions linked to the TPS concept and
materials identified
Many results can be applied to future specific mission and system analyses and for the
design of wind tunnel and flight drop tests