TPS Selection and Sizing Tool Implemented in  an Advanced Engineering Environment

McGuire, M. Kathleen; Bowles, Jeffrey V.; Yang, Lily; Kinney, David J.; Roberts, Cathy

doi:10.2514/6.2004-342

Cited by 14 publications

(5 citation statements)

References 1 publication

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“…TPS material selection criteria were based on expected heating environments with margins. The TPSSizer software 21 is used to perform the design. The TPS design employs a rigid outer aeroshell with the TPS bonded to the structure.…”

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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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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“…The back shell of the probe was not modeled or analyzed. The TPS analysis was performed using TPSSizer [26] which uses the ablative thermal analysis code FIAT. For all PICA runs, the material thicknesses were PICA, 0.02 cm RTV-560, 0.14 cm SIP (Strain Isolation Pad), 0.02 cm RTV-560 and the structure.…”

Section: W/cm2mentioning

confidence: 99%

Atmospheric entry studies for Uranus

Agrawal

Allen

Sklyanskiy

et al. 2014

2014 IEEE Aerospace Conference

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The present paper describes parametric studies conducted to define the Uranus entry trade space. Two different arrival opportunities in 2029 and 2043, corresponding to launches in 202 1 and 2034, respectively, are considered in the present study. These two launch windows factor in the 84-year orbital period, significant axial tilt, and the wide ring system of Uranus. As part of this study, an improved engineering model is developed for the Uranus atmosphere. This improved model is based on reconciliation of data available in the published literature and covers an altitude range of 0 km (1 bar pressure) to 5000 km. Two different entry scenarios are considered: 1) direct ballistic entry, and 2) aerocapture followed by entry from orbit. For ballistic entry a range of entry flight path angles are considered for probe entry masses ranging from 130 kg to 300 kg and diameters ranging from 0.8 m (Pioneer-Venus small probe scale) to 1.3 m (Galileo scale). The larger probes, which offer a larger packing volume, are considered in an attempt to accommodate more scientific instruments.For aerocapture a single case is studied to explore the feasibility and benefits of this option.

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“…To assess the thermal protection system (TPS), the nominal trajectory for each shape is generated and its aerodynamic and aeroheating characteristics, including the time history of the heating environments, are provided to the TPSSizer [13] set of programs. TPSSizer includes the FIAT [14] thermal analysis code for ablative TPS materials.…”

Section: E Thermal Protection System Sizingmentioning

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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TPS Selection and Sizing Tool Implemented in an Advanced Engineering Environment

Cited by 14 publications

References 1 publication

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

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

Atmospheric entry studies for Uranus

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

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