On Heatshield Shapes for Mars Entry Capsules

Prabhu, Dinesh K.; Saunders, David

doi:10.2514/6.2012-399

Cited by 7 publications

(3 citation statements)

References 15 publications

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“…The study presented in this paper considers a single geometry (shown in Fig. 3) based on previous missions and numerical investigations [23,50]. The vehicle shape is representative of a generic hypersonic re-entry geometry, a 30…”

Section: Resultsmentioning

confidence: 99%

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

2020

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This paper presents results of a system study of transpiration cooled thermal protection systems for Earth re-entry. The cooling performance for sustained hypersonic flight and transient re-entry of a blunt cone geometry is assessed. A simplified numerical model is used to calculate the transient temperature of a transpiration cooled heat shield. The performance of transpiration cooling is assessed by calculating the overall required coolant mass for different steady state and transient flight scenarios. Spatially and temporally optimised mass injection is presented for various flight conditions. The majority of the injection is required on the spherical nose segment of the blunted cone. Carbon/Carbon composite ceramic and the ultra high temperature ceramic Zirconium diboride are considered as wall materials. Both materials require similar amounts of coolant injection. In continuous hypersonic cruise, transpiration cooling is highly effective for flight conditions with velocities below 8 km s −1 and altitudes above 40 km. For transient re-entry, transpiration cooling is most viable for trajectories of entry velocities below 8.5 km s −1 and ballistic coefficients below 2.1 kg m −2. Nomenclature A Area, m 2 C D Drag coefficient c p Specific heat capacity, J kg −1 K −1

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Section: Resultsmentioning

confidence: 99%

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

2020

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“…Studies have shown that the eliminating the discontinuity in curvature between the nose cap and cone frustum results in a favorable pressure gradient over the entire lee-side (when flown at an angle of attack similar to MSL), and avoids increased turbulent heating due to the sonic line attachment at the cap/cone junction. 9) Based on data on similar spherical aeroshell capsule shapes, a series of ballistic coefficients were selected for analysis in the current study (see Table 2). The corresponding entry mass at Mars (based on a nominal hypersonic drag coefficient of 1.46) is also shown.…”

Section: Aeroshellmentioning

confidence: 99%

Supersonic Retro-Propulsion for Future High-Mass Robotic Mars Lander Missions

Lobbia

Wolf

Whetsel

2019

AEROSPACE TECHNOLOGY JAPAN

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A feasibility study was conducted to investigate the potential performance advantages of Supersonic Retro-Propulsion in support of future high-mass Mars robotic landing missions. A notional reference architecture for a potential future Mars Sample Return formed the basis for assuming a 4.7 m diameter SRP entry vehicle containing the Mars Ascent Vehicle element. Configuration analysis was conducted to ensure that the payload and required SRP components (including engines and propellant) fit within in the capsule volume. Optimized trajectory analysis highlighted several key performance sensitivities of SRP for ballistic coefficients of 150, 300, and 450 kg/m 2. These results indicated a broad SRP ignition envelope (1-4 km altitude, 300-750 m/s velocity), as well as relatively small propellant mass fraction sensitivities to SRP thrust/weight, landing site elevation, and the application of a 4-g entry deceleration constraint (relevant for future crewed mission trajectories). Finally, mass-sizing was performed to assess sensitivities to ballistic coefficient and entry velocity, and showcased the ability of the SRP system to land payload masses on the order of twice that of MSL.

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“…Atmospheric entry refers to the movement of human made or natural objects as they enter the atmospheric of a planet from outer space, in the case of Earth from an altitude above the "edge of space" [2]. The vehicle which enters into the atmospheric conditions from the outer space is known as Entry Vehicle.…”

Section: Introductionmentioning

confidence: 99%

CFD Analysis of Mars Phoenix Capsules at Mach Number 10

Raju¹

2015

J Aeronaut Aerospace Eng

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Numerical simulations are performed for flow over Phoenix entry vehicle at Mars at zero angle of Attack and Mach number 10. Flow field features like bow shock, shear layers, expansion fan and separation bubble will be captured using CFD commercial package FLUENT. The computed wall data of pressure and temperature will be compared with experimental results at Mars atmospheric conditions. This project deals with the study of flow over Phoenix entry vehicle at Mach number 10. The concept of atmospheric entry has applications in various fields. Vehicles that typically undergo this process include exo-orbital trajectories. In this project, the type of entry vehicle considered is entry capsule, which enters Mars atmosphere from an orbit. The primary design consideration of entry capsule requires large spherical nose radius of their fore body that gives high aerodynamic drag and a short body length for reducing the total structural weight and the ballistic coefficient.

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On Heatshield Shapes for Mars Entry Capsules

Cited by 7 publications

References 15 publications

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

Supersonic Retro-Propulsion for Future High-Mass Robotic Mars Lander Missions

CFD Analysis of Mars Phoenix Capsules at Mach Number 10

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