Afterbody Aeroheating Flight Data for Planetary Probe Thermal Protection System Design

Wright, Michael J.; Milos, Frank S.; Tran, P.

doi:10.2514/1.17703

Cited by 45 publications

(34 citation statements)

References 32 publications

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“…Beyond the neck is the far wake, which extends for many body diameters downstream as the momentum deficit created by the passing capsule is slowly recovered. In a hypersonic flow, the wake is oriented parallel to the freestream velocity vector, as seen in Figure 13 [18]. Next results are reported in Figure 14, where the comparison between static temperature contours for perfect gas (a) and nonequilibrium gas computations (b) at M ∞ = 20 and α = 20 deg is shown.…”

Section: Reactionmentioning

confidence: 81%

Aerodynamic Analysis of a Manned Space Vehicle for Missions to Mars

Pezzella

Viviani²

2011

Journal of Thermodynamics

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The paper deals with the aerodynamic analysis of a manned braking system entering the Mars atmosphere with the aim to support planetary entry system design studies. The exploration vehicle is an axisymmetric blunt body close to the Apollo capsule. Several fully three-dimensional computational fluid dynamics analyses have been performed to address the capsule aerodynamic performance. To this end, a wide range of flow conditions including reacting and nonreacting flow, different angles of attack, and Mach numbers have been investigated and compared. Moreover, nonequilibrium effects on the flow field around the entry vehicle have also been investigated. Results show that real-gas effects, for all the angles of attack considered, increase both the aerodynamic drag and pitching moment whereas the lift is only slighted affected. Finally, results comparisons highlight that experimental and CFD aerodynamic findings available for the Apollo capsule in air adequately represent the static coefficients of the capsule in the Mars atmosphere.

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Section: Reactionmentioning

confidence: 81%

Aerodynamic Analysis of a Manned Space Vehicle for Missions to Mars

Pezzella

Viviani²

2011

Journal of Thermodynamics

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“…Currently, there is a limited amount of relevant capsule afterbody re-entry heating data. [10][11][12][13][14] It is important to collect experimental data on complex flowfields such as this one to help validate computational fluid dynamics (CFD) models. 15,16 …”

Section: Introductionmentioning

confidence: 99%

NO PLIF Visualizations of the Orion Capsule in LENS-I

Combs

Clemens

Danehy

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…The Apollo Program took place during the 1960"s and saw several successful flight tests which were all carried out to acquire data on the heating loads experienced during a lunar re- vehicles re-entered the atmosphere at orbital velocities while the Apollo 4 and 6 were able to achieve super-orbital velocities by using a kick-stage (Wright, Milos, & Tran, 2006). The super-orbital velocities achieved by the Apollo 4 and Apollo 6 more closely resembled an atmospheric re-entry from a lunar return.…”

Section: Past Flight Experiments Apollo Programmentioning

confidence: 99%

“…According to Wright, Milos, and Tran (2006), the results of these four flight experiments serve as the best flight entry database to date.…”

Section: Past Flight Experiments Apollo Programmentioning

confidence: 99%

“…Two dedicated flight experiments were launched, FIRE I and FIRE II, during the early 60"s. The objective of Project FIRE was to develop our understanding of the heating that occurs during a lunar return into Earth"s atmosphere (Wright, Milos, & Tran, 2006). The FIRE capsules re-entered Earth"s atmosphere at 11.3 km/s, akin to a lunar return.…”

Section: Fire I and Iimentioning

confidence: 99%

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Design of a re-entry experiment to measure aeroshell heating rates

Guy¹

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A conceptual design review was conducted on a proposed sub-scale re-entry flight experiment. Through some statistical analysis, it was found that a fleet of 8 to 17 of the nonrecoverable re-entry capsules would be required for there to be a 95% chance of the fleet successfully carrying out a re-entry mission. The proposed capsule designs make use of a non-recoverable design. As such, it should be possible to quickly develop a small fleet of them.The experiment design looks at replicating the heat loads experienced during the hypersonic re-entry into Earth"s atmosphere after returning from an interplanetary mission. The re-entry velocity was taken to be 16 km/s. Analysis of the resultant heat loads during atmospheric entry at this speed dictated the aeroshell size. It was shown that the extremely high aerothermodynamic heating can be effectively managed through aeroshell geometry and material selection.

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Afterbody Aeroheating Flight Data for Planetary Probe Thermal Protection System Design

Cited by 45 publications

References 32 publications

Aerodynamic Analysis of a Manned Space Vehicle for Missions to Mars

Aerodynamic Analysis of a Manned Space Vehicle for Missions to Mars

NO PLIF Visualizations of the Orion Capsule in LENS-I

Design of a re-entry experiment to measure aeroshell heating rates

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