A High-Heritage Blunt-Body Entry, Descent, and Landing Concept for Human Mars Exploration

Price, Hoppy; Manning, Robert M.; Sklyanskiy, Evgeniy; Braun, Robert D.

doi:10.2514/6.2016-0219

Cited by 13 publications

(10 citation statements)

References 7 publications

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“…Therefore, EDLAS Phase 2 added the capsule concept to the vehicle configuration evaluations to determine the feasibility of the design to accommodate the HEOMD defined payload configurations [1]. Figure 7 shows several shapes shape options, including the Apollo [6], Apollo D-2 [7], and Soyuz backshell shapes considered for the study. The Soyuz shape was selected to maximize payload volume.…”

Section: B Capsulementioning

confidence: 99%

Human Mars Entry, Descent, and Landing Architecture Study: Rigid Decelerators

Polsgrove

Percy

García

et al. 2018

2018 AIAA SPACE and Astronautics Forum and Exposition

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Several technology investments are required to develop Mars human scale Entry, Descent, and Landing (EDL) systems. Studies play the critical role of identifying the most feasible technical paths and high payoff investments. The goal of NASA's Entry, Descent and LandingArchitecture Study is to inform those technology investments. In Phase 1 of the study, a point design for one lifting-body-like rigid decelerator vehicle, was developed. In Phase 2, a capsule concept was also considered to determine how it accommodated the human mission requirements. This paper summarizes the concept of operations for both rigid vehicles to deliver a 20-metric ton (t) payload to the surface of Mars. Details of the vehicle designs and flight performance are presented along with a packaging, mass sizing, and a launch vehicle fairing assessment. Finally, recommended technology investments based on the analysis of the rigid vehicles are provided.

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Section: B Capsulementioning

confidence: 99%

Human Mars Entry, Descent, and Landing Architecture Study: Rigid Decelerators

Polsgrove

Percy

García

et al. 2018

2018 AIAA SPACE and Astronautics Forum and Exposition

View full text Add to dashboard Cite

show abstract

“…program, which showed that the technology exists to decelerate and land heavy vehicles from supersonic conditions using rocket thrusters. [21]. T H B 3 is the reconstructed…”

Section: Reference Edl Mission Designmentioning

confidence: 99%

“…whereas an average ISP of 325 s is applied in the simulation considering a loss in efficiency during the supersonic-retropropulsion (SRP) phase [21].…”

Section: Supersonic Retro-propulsion Modelingmentioning

confidence: 99%

“…To qualify flexible shield results this survey aims to compare given outcomes to an approach using a high BC entry. Price, Manning, Sklyanskiy and Braun [21] recently proposed a radical departure from conventional EDL mission strategies with a concept to adopt a high BC initial entry of A major strength of the methodology adopted in this study is that it enables comparison of mission designs with different Φ shield and payloads. Hence for each viable technology (with an associated Φ shield ) an optimum BC exists in terms of entry mass efficiency.…”

Section: Mission Analysis: Human Mars Missionmentioning

confidence: 99%

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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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“…supersonic retropropulsion (SRP)). 1,2 Significant work remains to characterize these flows and to design systems capable of human class missions to Mars.…”

Section: Introductionmentioning

confidence: 99%

Advancing Supersonic Retropropulsion Using Mars-Relevant Flight Data: An Overview

Braun¹,

Sforzo

Campbell

2017

AIAA SPACE and Astronautics Forum and Exposition

Self Cite

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Advanced robotic and human missions to Mars require landed masses well in excess of current capabilities. One approach to safely land these large payloads on the Martian surface is to extend the propulsive capability currently required during subsonic descent to supersonic initiation velocities. However, until recently, no rocket engine had ever been fired into an opposing supersonic freestream. In September 2013, SpaceX performed the first supersonic retropropulsion (SRP) maneuver to decelerate the entry of the first stage of their Falcon 9 rocket. Since that flight, SpaceX has continued to perform SRP for the reentry of their vehicle first stage, having completed multiple SRP events in Mars-relevant conditions in July 2017. In FY 2014, NASA and SpaceX formed a three-year public-private partnership centered upon SRP data analysis. These activities focused on flight reconstruction, CFD analysis, a visual and infrared imagery campaign, and Mars EDL design analysis. This paper provides an overview of these activities undertaken to advance the technology readiness of Mars SRP.

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A High-Heritage Blunt-Body Entry, Descent, and Landing Concept for Human Mars Exploration

Cited by 13 publications

References 7 publications

Human Mars Entry, Descent, and Landing Architecture Study: Rigid Decelerators

Human Mars Entry, Descent, and Landing Architecture Study: Rigid Decelerators

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

Advancing Supersonic Retropropulsion Using Mars-Relevant Flight Data: An Overview

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