Organizational Unit:
Daniel Guggenheim School of Aerospace Engineering

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Start date: 2012 × Item Type: Publication × Has files: Yes × search.filters.applied.f.isSeriesOfPublicationTitle: International Planetary Probe Workshop (IPPW) ×

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Now showing 1 - 4 of 4
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    BioDOME: Concept of an EDL System for Returning Small Biological Samples from LEO
    (Georgia Institute of Technology, 2015-06) Rossman, Grant ; LeVine, Matthew ; Lawlor, Sean ; Sloss, Tyler ; Mishra, Pranay ; Tan, Zu Puayen ; Braun, Robert D.
    A conceptual design of an Earth return vehicle is presented with the goal of safely returning biological samples from orbit. Key entry, descent, and landing trade studies were completed at the conceptual level for two different mission scenarios: return from the International Space Station (ISS) and an autonomous, free-flying vehicle returning from Low Earth Orbit (LEO). The analyses that follow for each key subsystem drove design decisions to create the Biopan Deployment in Orbit for Microgravity Exposure (BioDOME) vehicle with the versatility to satisfy both of the aforementioned mission scenarios. The final design features a ballistic entry, a 45 ◦ spherecone aeroshell with a diameter of 88-cm, a PICA heatshield with a thickness of 7.7 cm, and a passive landing system containing an 8-m diameter ringsail parachute combined with a 7.8-cm thick crushable carbon foam. Analysis of the vehicle performance verified survivability of biological samples due to heat and deceleration loads from entry. Trajectory dispersion analysis yielded crossrange and downrange limited to ±1.5-km and ±30-km, respectively, while landing velocity was confirmed to be ≤ 4.0-m/s for all cases.
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    Integrated Trajectory, Atmosphere, and Aerothermal Reconstruction Methodology Using the MEDLI Dataset
    (Georgia Institute of Technology, 2012-06) Dutta, Soumyo ; Mahzari, Milad ; White, Todd R. ; Braun, Robert D.
    The Mars Science Laboratory (MSL) mission’s instrumentation will enable accurate reconstruction of the vehicle’s entry, descent, and landing (EDL) performance including the trajectory, the observed atmosphere, aerodynamics, aeroheating, and heatshield material response. The objective of this paper is to develop methodologies for an integrated approach to the reconstruction of the vehicle’s EDL performance. Two estimation approaches are presented: Serial and Concurrent. The serial approach is demonstrated by application to the Mars Pathfinder flight data and estimating trajectory and aeroheating performance.
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    Mass Model Development for Conceptual Design of a Hypersonic Rigid Deployable Decelerator
    (Georgia Institute of Technology, 2012-06) Cruz-Ayoroa, Juan G. ; Kazemba, Cole D. ; Steinfeldt, Bradley A. ; Kelly, Jenny R. ; Clark, Ian G. ; Braun, Robert D.
    As the required payload masses for planetary entry systems increase, innovative entry vehicle decelerator systems are becoming a topic of interest. With this interest comes a growing need for the capability to characterize the performance of such decelerators. This work proposes a first-order mass model for fully-rigid deployable decelerator systems. The analytical methodology that is presented can be applied to a wide range of entry conditions and material properties for rapid design space exploration. The tool is applied to a case study of a C/SiC hot structure decelerator at Mars for comparison to the performance of the Hypersonic Inflatable Aerodynamic Decelerator concepts presented in a recent EDL-SA study. Results show that the performance of a rigid deployable structure can be comparable to that of a Hypersonic Inflatable Aerodynamic Decelerator at high entry ballistic coefficients and small decelerator diameters.
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    Conceptual Modeling of Supersonic Retropropulsion Flow Interactions and the Relationship to System Performance
    (Georgia Institute of Technology, 2012-06) Korzun, Ashley M. ; Braun, Robert D.
    Supersonic retropropulsion is an entry, descent, and landing technology applicable to and potentially enabling the high-mass missions to the surface required for advanced robotic and human exploration at Mars. For conceptual design, an initial understanding of the significance of retropropulsion configuration on the vehicle’s static aerodynamic characteristics and the relation of this configuration to other vehicle performance metrics that traditionally determine vehicle configuration is necessary. This work develops an approximate model for the aerodynamic - propulsive flow interaction based on momentum transfer within the flowfield and the geometry of relevant flow structures. This model is used to explore the impact of operating conditions, required propulsion system performance, propulsion system composition, and vehicle configuration on the integrated aerodynamic drag characteristics of full-scale vehicles for Mars entry, descent, and landing. Conclusions are then drawn on the fidelity and effort required to support specific design trades for supersonic retropropulsion.