Aerothermodynamic Environments Definition for the Mars Science Laboratory Entry Capsule

Edquist, Karl T.; Dyakonov, Artem A.; Wright, Michael J.; Tang, Chun

doi:10.2514/6.2007-1206

Cited by 55 publications

(45 citation statements)

References 31 publications

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“…The location and magnitude of augmented heating are a function of the oncoming flow field and are sensitive to the computational grid density. Steady-state CFD of an earlier design 77 indicated that the presence of an RCS plume could cause transient localized heating about 3-5 times larger than the baseline levels as shown in Fig. 14.…”

Section: Singularity Heatingmentioning

confidence: 99%

“…77 An experimental program was followed for MSL that provided some of the data needed to anchor the CFD tools and understand the physics of turbulent transition and heating augmentation for 70-deg sphere-cones. 77 These tests (discussed further in Section 8 below) have demonstrated that the high turbulent heating rates predicted on the leeside of the cone are real and must be accounted for during the design of the TPS for the Mars Science Laboratory.…”

Section: Transition and Turbulent Heatingmentioning

confidence: 99%

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A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The current status of aerothermal analysis for Mars entry missions is reviewed. The aeroheating environment of all Mars missions to date has been dominated by convective heating. Two primary uncertainties in our ability to predict forebody convective heating are turbulence on a blunt lifting cone and surface catalysis in a predominantly CO2 environment. Future missions, particularly crewed vehicles, will encounter additional heating from shock-layer radiation due to a combination of larger size and faster entry velocity. Localized heating due to penetrations or other singularities on the aeroshell must also be taken into account. The physical models employed to predict these phenomena are reviewed, and key uncertainties or deficiencies inherent in these models are explored.

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Section: Singularity Heatingmentioning

confidence: 99%

Section: Transition and Turbulent Heatingmentioning

confidence: 99%

A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…To accomplish a precision landing, the vehicle will be required to fly a controlled lifting trajectory; current designs call for a lift-to-drag ratio (L/D) of 0.24, which will be generated by flying at an angle-of-attack of -16 deg. As a result of its high ballistic coefficient, MSL will experience heating levels higher than any of the previous missions, and furthermore, because of the high angle-of-attack (for a blunt body) flight requirement, the flow over the leeside of the forebody is expected to become turbulent early in the trajectory, which will substantially augment both the heating rates and loads above the laminar levels 3 .…”

Section: Introductionmentioning

confidence: 99%

Turbulent Aeroheating Testing of Mars Science Laboratory Entry Vehicle

Hollis

Collier²

2008

Journal of Spacecraft and Rockets

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“…A companion paper 7 covers design environments for the entry capsule heatshield. Previous computational 8,9 and experimental 10−12 aerothermodynamics analyses have been performed for various MSL aeroshell configurations and design trajectories. This paper covers the analysis used to support flight TPS hardware development for the original 2009 launch opportunity.…”

Section: Nasa's Mars Science Laboratory (Msl) Entry Systemmentioning

confidence: 99%

Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute Cone

Edquist

Dyakonov

Wright

et al. 2009

41st AIAA Thermophysics Conference

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Aerothermodynamic design environments are presented for the Mars Science Laboratory entry capsule backshell and parachute cone. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux) design entry trajectories from a 2009 launch. Transient interference effects from reaction control system thruster plumes were included in the design environments when necessary. The limiting backshell design heating conditions of 6.3 W/cm 2 for heat flux and 377 J/cm 2 for total heat load are not influenced by thruster firings. Similarly, the thrusters do not affect the parachute cover lid design environments (13 W/cm 2 and 499 J/cm 2 ). If thruster jet firings occur near peak dynamic pressure, they will augment the design environments at the interface between the backshell and parachute cone (7 W/cm 2 and 174 J/cm 2 ). Localized heat fluxes are higher near the thruster fairing during jet firings, but these areas did not require additional thermal protection material. Finally, heating bump factors were developed for antenna radomes on the parachute cone.lift-to-drag ratio m entry system mass (kg) p pressure (Earth atm, 1 Earth atm = 101,325 P a)

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Aerothermodynamic Environments Definition for the Mars Science Laboratory Entry Capsule

Cited by 55 publications

References 31 publications

A Review of Aerothermal Modeling for Mars Entry Missions

A Review of Aerothermal Modeling for Mars Entry Missions

Turbulent Aeroheating Testing of Mars Science Laboratory Entry Vehicle

Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute Cone

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