Human Mars mission design study utilizing the adaptive deployable entry and placement technology

“…Common configurations of mechanically deployable aeroshells are umbrellalike (see Fig. 2), demonstrated by the IRENE [8] and Adaptable, Deployable, Entry and Placement Technology (ADEPT) [9] projects, set up by ESA and NASA, respectively. These designs are effective for their uniform deployment and compact stowed configuration.…”

Section: Introductionmentioning

confidence: 99%

Design and Dynamic Analysis of Rigid Foldable Aeroshells for Atmospheric Entry

O'Driscoll

Bruce

Santer

2021

Journal of Spacecraft and Rockets

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“…The three entry concepts include two low lift-to-drag (L/D) ratio, low ballistic number vehicles including the Adaptive Deployable Entry and Placement Technology (ADEPT) [3] and the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) [4,5]. For these entry systems payload elements are arranged vertically in the launch vehicle.…”

Section: Entry and Descent At Marsmentioning

confidence: 99%

Impacts of launch vehicle fairing size on human exploration architectures

Jefferies

Collins

Cianciolo

et al. 2017

2017 IEEE Aerospace Conference

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Human missions to Mars, particularly to the Martian surface, are grand endeavors that place extensive demands on ground infrastructure, launch capabilities, and mission systems. The interplay of capabilities and limitations among these areas can have significant impacts on the costs and ability to conduct Mars missions and campaigns. From a mission and campaign perspective, decisions that affect element designs, including those based on launch vehicle and ground considerations, can create effects that ripple through all phases of the mission and have significant impact on the overall campaign. These effects result in impacts to element designs and performance, launch and surface manifesting, and mission operations.In current Evolvable Mars Campaign concepts, the NASA Space Launch System (SLS) is the primary launch vehicle for delivering crew and payloads to cis-lunar space. SLS is currently developing an 8.4m diameter cargo fairing, with a planned upgrade to a 10m diameter fairing in the future. Fairing diameter is a driving factor that impacts many aspects of system design, vehicle performance, and operational concepts. It creates a ripple effect that influences all aspects of a Mars mission, including: element designs, grounds operations, launch vehicle design, payload packaging on the lander, launch vehicle adapter design to meet structural launch requirements, control and thermal protection during entry and descent at Mars, landing stability, and surface operations.Analyses have been performed in each of these areas to assess and, where possible, quantify the impacts of fairing diameter selection on all aspects of a Mars mission. Several potential impacts of launch fairing diameter selection are identified in each of these areas, along with changes to system designs that result. Solutions for addressing these impacts generally result in increased systems mass and propellant needs, which can further exacerbate packaging and flight challenges. This paper presents the results of the analyses performed, the potential changes to mission architectures and campaigns that result, and the general trends that are more broadly applicable to any element design or mission planning for human exploration.

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“…The bottom layers of the cloth carry the aerodynamic load while the top layers manage the thermal energy. A detailed description is given in Cassel et al [7].…”

Section: Adept-mentioning

confidence: 99%

Human Mars EDL pathfinder study: Assessment of technology development gaps and mitigations

Lillard

Olejniczak

2017

2017 IEEE Aerospace Conference

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This paper presents the results of a NASA initiated Agency-wide assessment to better characterize the risks and potential mitigation approaches associated with landing human class Entry, Descent, and Landing (EDL) systems on Mars. Due to the criticality and long-lead nature of advancing EDL techniques, it is necessary to determine an appropriate strategy to improve the capability to land large payloads. A key focus of this study was to understand the key EDL risks and with a focus on determining what "must" be tested at Mars. This process identified the various risks and potential risk mitigation strategies along with the key near term technology development efforts required and in what environment those technology demonstrations were best suited. The study identified key risks along with advantages to each entry technology. In addition, it was identified that provided the EDL concept of operations (con ops) minimized large scale transition events, there was no technology requirement for a Mars pre-cursor demonstration. Instead, NASA should take a direct path to a human-scale lander.

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Human Mars mission design study utilizing the adaptive deployable entry and placement technology

Cited by 15 publications

References 8 publications

Design and Dynamic Analysis of Rigid Foldable Aeroshells for Atmospheric Entry

Design and Dynamic Analysis of Rigid Foldable Aeroshells for Atmospheric Entry

Impacts of launch vehicle fairing size on human exploration architectures

Human Mars EDL pathfinder study: Assessment of technology development gaps and mitigations

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