Mars Pathfinder Heatshield Design and Flight Experience

Willcockson, William H.

doi:10.2514/2.3456

Cited by 46 publications

(12 citation statements)

References 4 publications

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“…The conditions at the Backshell Hip are less severe (5.2 W/cm 2 and 245 J/cm 2 ). As a comparison, the Pathfinder SLA-561V heatshield 13 (0.75 in) survived much more severe heating environments…”

Section: E Design Environmentsmentioning

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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Section: E Design Environmentsmentioning

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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“…It is assumed that the backup wall is attached to the back surface of the ablator by an adhesive, where the allowable maximum temperature value of the adhesive Tb_allow is 250°C (=523.15K=480F). 18) (The allowable maximum temperatures of the backup wall and the ablator are assumed more than Tb_allow.) Because the thickness of the adhesive is assumed to be very small, the adhesive was neglected in the analysis and the calculated ablator back surface temperature is regarded as the adhesive temperature.…”

Section: Parametric Study and Conditions Of The Analysismentioning

confidence: 99%

Study of the Effects of Heat Load, Ablator Density and Backup Structure upon the Thermal Protection Performance of Heat Shield Systems Consisting of Phenolic Carbon Ablators

Kato

Matsuda

Okuyama

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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The effects of heat load, ablator density, and backup structure, etc. upon the heat shield performance of the lightweight phenolic carbon ablators named LATS were investigated using a one-dimensional ablation analysis code. The ablator density was assumed to be from about 260 to 1000kg/m 3 . Heat flux time histories of a rectangular pattern were assumed, where cases of constant heating duration time and constant accumulated heat load (up to 600MJ/m 2 ) were considered. The heating level was assumed to be from 1 to 10MW/m 2 , which means that the ablator surface is in the region of diffusion control oxidation/sublimation. The materials of the backup wall are assumed to be aluminum, stainless steel and high density CFRP. Main findings are: (1) For a low heat flux q with the same heating duration time tq, the necessary thickness, with which the maximum back surface temperature equals to the pre-determined allowable temperature, is nearly constant as the density v changes. On the other hand, the necessary thickness increases largely when q is larger and v is smaller. The ablator necessary mass increases with the increase of v and q for the same tq.

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“…The baseline ERC forebody TPS is unipiece PICA (Phenolic Impregnated Carbon Ablator; [25,26,29]) manufactured by FMI (with ARC insight and oversight) for Stardust. It was flown in 2006 at entry heating conditions twice those expected by MarcoPolo-R.…”

Section: Earth Re-entry Capsule (Erc)mentioning

confidence: 99%

MarcoPolo-R near earth asteroid sample return mission

et al. 2011

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Exp Astron (2012) 33:645-684 return a unique sample to Earth unaltered by the atmospheric entry process or terrestrial weathering. MarcoPolo-R will return bulk samples (up to 2 kg) from an organic-rich binary asteroid to Earth for laboratory analyses, allowing us to: explore the origin of planetary materials and initial stages of habitable planet formation; identify and characterize the organics and volatiles in a primitive asteroid; understand the unique geomorphology, dynamics and evolution of a binary NEA. This project is based on the previous Marco Polo mission study, which was selected for the Assessment Phase of the first round of Cosmic Vision. Its scientific rationale was highly ranked by ESA committees and it was not selected only because the estimated cost was higher than the allotted amount for an M class mission. The cost of MarcoPolo-R will be reduced to within the ESA medium mission budget by collaboration with APL (John Hopkins University) and JPL in the NASA program for coordination with ESA's Cosmic Vision Call. The baseline target is a binary asteroid (175706) 1996 FG3, which offers a very efficient operational and technical mission profile. A binary target also provides enhanced science return. The choice of this target will allow new investigations to be performed more easily than at

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Mars Pathfinder Heatshield Design and Flight Experience

Cited by 46 publications

References 4 publications

Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute Cone

Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute Cone

Study of the Effects of Heat Load, Ablator Density and Backup Structure upon the Thermal Protection Performance of Heat Shield Systems Consisting of Phenolic Carbon Ablators

MarcoPolo-R near earth asteroid sample return mission

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