Aerothermal Anchoring of CBAERO Using High Fidelity CFD

Kinney, David J.

doi:10.2514/6.2007-608

Cited by 33 publications

(8 citation statements)

References 10 publications

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“…The anchoring approach addresses the deficiencies with the engineering and high fidelity methods by utilizing a rapid and intelligent engineering-based interpolation method. Further detail of this anchoring approach can be found in Reference [10]. …”

Section: B Aerodynamics/aerothermodynamicsmentioning

confidence: 99%

Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry

Garcia

Brown

Kinney

et al. 2010

10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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As NASA continues to make plans for future robotic precursor and eventual human missions to Mars, the need to characterize and develop designs for entry vehicles capable of delivering large masses to the surface of Mars will persist. In combination with this, NASA has recognized that the current heritage technology for Mars' Entry Decent and Landing (EDL) does not have the capability to land the required payload masses. Both the Thermal Protection System (TPS) and the Descent/Landing systems require new design approaches. Because of these needs, NASA has performed an Entry, Descent and Landing Systems Analysis (EDL-SA) study for high mass exploration and science missions to identify key enabling technology areas for further investment. One key technology area identified includes rigid aeroshell shapes for aerodynamic performance and controllability.In this investigation, a system optimization study of alternative aeroshell shapes for Mars exploration class payloads of approximately 40 metric tons has been conducted. This system optimization is accomplished using a Multi-disciplinary Design Optimization (MDO) framework which accounts for the aeroshell shape, trajectory, thermal protection system, and vehicle subsystem closure along with a Multi Objective Genetic Algorithm (MOGA) for the initial shape exploration. This is accomplished using a combination of engineering analysis and higher-fidelity physics based tools along with optimization methods and engineering judgment. The results of this process have shown that a proposed family of optimized mid lift-to-drag aeroshell shapes exhibit a significant improvement to the current reference entry rigid aeroshell configuration. Furthermore, a trade-off between the vehicle TPS and structural mass is identified for this class of aeroshell shapes and their corresponding trajectories. Balancing this trade-off can yield an overall decrease in the total vehicle mass or corresponding increase in landed payload, as compared to the current reference configuration. NomenclatureA = Effective projected vehicle area CD = Drag coefficient CDa = Drag Area, m 2 CL = Lift coefficient Cm = Pitching moment coefficient Cm α = Pitching moment coefficient curve slope variation with angle-of-attack, /deg. 0 = Earth's gravity constant (g 0 = 9.80665 m/s2) Isp = Specific impulse, sec (on earth) L B = Body Length, m L B_REF = Reference Body Length, m L/D = Lift-to-drag ratio m_Entry = Entry Mass, kg m_Entry REF = Reference Entry Mass, kg m payload = Payload mass, kg MaxQdot = Maximum Heat flux on the body, W/cm 2 qmax = Maximum dynamic pressure, Pa hload = Integrated heatload, J/cm 2 Re = Reynolds Number RCS = Reaction Control System RSS = Root Sum Square Swet = Wetted vehicle surface area, m 2 TPS = Thermal Protection System UWT_Body REF = Reference body structural areal mass M ∞ = Free-stream Mach number αtrim = Trim angle-of-attack, deg. ρ ∞ = Free-stream density, kg/m 3

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Section: B Aerodynamics/aerothermodynamicsmentioning

confidence: 99%

Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry

Garcia

Brown

Kinney

et al. 2010

10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

Self Cite

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“…To determine atmospheric properties along trajectories, the ESA Mars Climate Database 5.2 is used [15]. Figure 5 shows results for pressure distribution across the heat shield area for the Orion lens computed with the presented code (NewAero3D) in comparison with the widely used industrial tool CBAERO [16].…”

Section: Computational Frameworkmentioning

confidence: 99%

“…Three dimensional pressure distribution for the Orion lens heat shield, Mach 32.2 and 23 degree AoA, reference from[16].…”

mentioning

confidence: 99%

Strategies to utilize advanced heat shield technology for high-payload mars atmospheric entry missions

2017

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Present Entry, Descent and Landing (EDL) technology for interplanetary missions does not have the capabilities to meet the demanding requirements that come with future missions. A popular target for such missions is Mars and today efforts are made to send manned as well as sophisticated robotic probes to the Martian surface. Because present EDL technology has reached its limits, fundamentally new approaches are needed to significantly extend capabilities. Systematic evaluation of novel EDL technologies and optimization of EDL strategies are crucial needs for conceptual design. A computational framework will be presented tailored to enable systematic EDL analysis with special regards to novel EDL technology and event strategies. The benefits of flexible heat shield concepts that come with liberties in the choice of the ballistic coefficient will be shown in comparison with solid shield alternatives for payload classes of 2, 25 and 40 tonnes to show potential for manned and robotic missions. Furthermore, benefits of the new methodology for novel EDL event strategies are presented and discussed. The introduced methodology will help designers exploit new directions for conceptual design regarding EDL systems in terms of entry mass optimization and mission capabilities

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“…Preliminary TPS materials selection and TPS sizing was performed based on the provided aeroheating environments and trajectories. The solutions were obtained by extrapolating from the provided inputs, and employing CFD-anchored aerothermal databases based on the CBAERO software 20 . TPS material selection criteria were based on expected heating environments with margins.…”

Section: G Thermal Protection Systemmentioning

confidence: 99%

A Rigid Mid Lift-to-Drag Ratio Approach to Human Mars Entry, Descent, and Landing

Cerimele

Robertson

Sostaric

et al. 2017

AIAA Guidance, Navigation, and Control Conference

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Current NASA Human Mars architectures require delivery of approximately 20 metric tons of cargo to the surface in a single landing. A proposed vehicle type for performing the entry, descent, and landing at Mars associated with this architecture is a rigid, enclosed, elongated lifting body shape that provides a higher lift-to-drag ratio (L/D) than a typical entry capsule, but lower than a typical winged entry vehicle (such as the Space Shuttle Orbiter). A rigid Mid-L/D shape has advantages for large mass Mars EDL, including loads management, range capability during entry, and human spaceflight heritage. Previous large mass Mars studies have focused more on symmetric and/or circular cross-section Mid-L/D shapes such as the ellipsled. More recent work has shown performance advantages for non-circular cross section shapes. This paper will describe efforts to design a rigid Mid-L/D entry vehicle for Mars which shows mass and performance improvements over previous Mid-L/D studies. The proposed concept, work to date and evolution, forward path, and suggested future strategy are described.

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Aerothermal Anchoring of CBAERO Using High Fidelity CFD

Cited by 33 publications

References 10 publications

Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry

Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry

Strategies to utilize advanced heat shield technology for high-payload mars atmospheric entry missions

A Rigid Mid Lift-to-Drag Ratio Approach to Human Mars Entry, Descent, and Landing

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