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Daniel Guggenheim School of Aerospace Engineering
Daniel Guggenheim School of Aerospace Engineering
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ItemBioDOME: 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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ItemIntegrated 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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ItemMass 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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ItemConceptual 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.
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ItemPerformance Characterization, Sensitivity and Comparison of a Dual Layer Thermal Protection System(Georgia Institute of Technology, 2011-06) Kazemba, Cole D. ; McGuire, Mary Kathleen ; Howard, Austin ; Clark, Ian G. ; Braun, Robert D.With the goal of landing high-mass cargo or crewed missions on Mars, NASA has been developing new thermal protection technologies with enhanced capability and reduced mass compared to traditional approaches. Two examples of new thermal protection system (TPS) concepts are dual layer and flexible TPS. Each of these systems introduces unique challenges along with potential performance enhancements. Traditional monolithic ablative TPS, which have been flown on every Mars robotic mission to date, use a single layer of ablative material. The new dual layer TPS concepts utilize an insulating layer of material beneath an ablative layer to increase efficiency and save mass. A study was conducted on the dual layer system to identify sensitivities in performance to uncertainties in material properties and aerothermal environments. A performance metric which is independent of the system construction was developed in order to directly compare the abilities and benefits between the traditional, dual layer and eventually, flexible systems. Using a custom MATLAB code enveloping the Fully Implicit Ablation and Thermal Response Program (FIAT), the required TPS areal mass was calculated for several different parametric scenarios. Overall TPS areal mass was found to be most sensitive to the constraining allowable temperature in each system and aerothermal heat transfer augmentation (attributed here to material surface roughness). From these preliminary results it was found that the nominal dual layer TPS construction investigated could produce improvements over a traditional TPS in the specified performance metric between 14-36%, depending on the flight environments and total integrated heat load expected.
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ItemStatistical Entry, Descent and Landing Performance Reconstruction of the Mars Phoenix Lander(Georgia Institute of Technology, 2011-06) Dutta, Soumyo ; Clark, Ian G. ; Russell, Ryan P. ; Braun, Robert D.The Phoenix Lander successfully landed on the surface of Mars on May 25, 2008. During the entry, descent and landing (EDL), the vehicle had instruments on-board that took sensed acceleration, angular rates and altimeter measurements. In this study, methodology used to reconstruct the trajectory and other EDL performance information using a statistical filter to process the observations from the sensors is demonstrated. A statistical filter estimates parameters simultaneously with the uncertainty in the estimates. The results presented here will include Phoenix’s event timeline, trajectory information, time-of-flight atmosphere and aerodynamic coefficients of an EDL subsystem as well as the uncertainty in the estimated states.
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ItemSubsonic and Transonic Wind Tunnel Testing of Two Inflatable Aerodynamic Decelerators(Georgia Institute of Technology, 2010-06) Tanner, Christopher L. ; Cruz, Juan R. ; Hughes, Monica F. ; Clark, Ian G. ; Braun, Robert D.Two inflatable aerodynamic decelerator designs were tested in the Transonic Dynamics Tunnel at the NASA Langley Research Center: a tension cone and an isotensoid. The tension cone consists of a flexible tension shell attached to a torus and the isotensoid employs a ram-air inflated envelope. Tests were conducted at Mach numbers from 0.3 to 1.08 and Reynolds numbers from 0.59 to 2.46 million. The main objective of these tests was to obtain static aerodynamic coefficients at subsonic and transonic speeds to supplement supersonic aerodynamic data for these same two designs. The axial force coefficients of both designs increased smoothly from subsonic through transonic Mach numbers. Dynamic data show significant oscillation of the tension cone and minimal oscillation of the isotensoid. The transonic and subsonic data will be used to assemble an inflatable decelerator aerodynamic database for use in computational analyses and system studies.
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ItemEntry, Descent, and Landing System Design for the Mars Gravity Biosatellite(Georgia Institute of Technology, 2008-06-26) Korzun, Ashley M. ; Smith, Brandon P. ; Yu, Chi-Yau ; Hartzell, Christine M. ; Hott, Kyle B. ; Place, Laura A. ; Braun, Robert D. ; Martinelli, Scott K.Mars Gravity Biosatellite is a novel program aimed at providing data on the effects of partial gravity on mammalian physiology. A collaboration between MIT and Georgia Tech, this student-developed free-flyer spacecraft is designed to carry a payload of 15 mice into low Earth orbit, rotating to generate accelerations equivalent to Martian gravity. After 35 days, the payload will re-enter the atmosphere and be recovered for study. Having engaged more than 500 students to date in space life science, systems engineering, and hardware development, the Mars Gravity Biosatellite program offers a unique, interdisciplinary educational opportunity to address a critical challenge in the next steps in human space exploration through the development of a free-flyer platform for partial gravity science with full entry, descent, and landing (EDL) capability. Execution of a full entry, descent, and landing from low Earth orbit is a rare requirement among university-class spacecraft. The EDL design for the Mars Gravity Biosatellite is driven by requirements on the allowable deceleration profile for a payload of de-conditioned mice and maximum allowable recovery time. The 260 kg entry vehicle follows a ballistic trajectory from low Earth orbit to a target recovery site at the Utah Test and Training Range. Reflecting an emphasis on design simplicity and the use of heritage technology, the entry vehicle uses the Discoverer aeroshell geometry and leverages aerodynamic decelerators for mid-air recovery and operations originally developed for the Genesis mission. This paper presents the student-developed EDL design for the Mars Gravity Biosatellite, with emphasis on trajectory design, dispersion analysis, and mechanical design and performance analysis of the thermal protection and parachute systems. Also included is discussion on EDL event sequencing and triggers, contingency operations, the deorbit of the spacecraft bus, plans for further work, and the educational impact of the Mars Gravity Biosatellite program.
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ItemIntroducing PESST: A Conceptual Design and Analysis Tool for Unguided/Guided EDL Systems(Georgia Institute of Technology, 2008-06-24) Otero, Richard ; Grant, Michael ; Steinfeldt, Brad ; Braun, Robert D.The Planetary Entry Systems and Synthesis Tool (PESST) has been under development at the Space Systems Design Laboratory (SSDL) for several years. This framework has the capability to estimate the performance and mass of a hypersonic vehicle using user-defined geometry, hypersonic aerodynamics, flight mechanics, selectable guidance, thermal response and mass estimation. Earth and Mars atmospheres are preloaded with the ability to also use either user-defined or GRAM atmospheric models. Trade studies can be performed by parameter sweeps to gain an excellent understanding of the design space for conceptual studies. This framework is broadly applicable to conceptual studies of EDL, aerocapture and precision and/or pin point landing systems.
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ItemEntry, Descent, and Landing System Design for the Mars Gravity Biosatellite(Georgia Institute of Technology, 2008-06) Korzun, Ashley M. ; Smith, Brandon P. ; Hartzell, Christine M. ; Yu, Chi-Yau ; Place, Laura A. ; Martinelli, Scott K. ; Braun, Robert D. ; Hott, Kyle B.Execution of a full entry, descent, and landing (EDL) from low Earth orbit is a rare requirement among university class spacecraft. Successful completion of the Mars Gravity Biosatellite mission requires the recovery of a mammalian payload for post-flight analysis of the effects of partial gravity. The EDL design for the Mars Gravity Biosatellite is driven by requirements on the allowable deceleration profile for a payload of deconditioned mice and maximum allowable recovery time. The 260 kg entry vehicle follows a ballistic trajectory from low Earth orbit to a target recovery site at the Utah Test and Training Range. Reflecting an emphasis on design simplicity and the use of heritage technology, the entry vehicle uses the Discoverer aeroshell geometry and leverages aerodynamic decelerators for mid-air recovery and operations originally developed for the Genesis mission. This paper presents the student-developed EDL design for the Mars Gravity Biosatellite, with emphasis on trajectory design, dispersion analysis, and mechanical design and performance analysis of the thermal protection and parachute systems. Also included is discussion on EDL event sequencing and triggers, the de-orbit of the spacecraft bus, plans for further work, and the educational impact of the Mars Gravity Biosatellite program.