Organizational Unit:
Space Systems Design Laboratory (SSDL)

Permanent Link
https://hdl.handle.net/1853/70747
Research Organization Registry ID
Description
Previous Names
Parent Organization
Parent Organization
Includes Organization(s)
ArchiveSpace Name Record
https://finding-aids.library.gatech.edu/agents/corporate_entities/1138

Filters

2011 - 2012 3
3
3
3
Reset filters

Settings
Type: Text × Author: Clark, Ian G. × Author: Kazemba, Cole D. ×

Publication Search Results

Now showing 1 - 3 of 3
  • Thumbnail Image
    Item
    Survey of Blunt Body Dynamic Stability in Supersonic Flow
    (Georgia Institute of Technology, 2012-08) Kazemba, Cole D. ; Braun, Robert D. ; Clark, Ian G. ; Schoenenberger, Mark
    This survey presents a comprehensive investigation of blunt body dynamic stability. An examination of the experimental, analytical, and computational methods for predicting dynamic stability characteristics, along with the deficiencies accompanying each method is presented. The observed influence of vehicle and environmental parameters on the resulting dynamic response is discussed. Additionally, the proposed physical mechanisms that may govern this complex phenomenon are introduced. There exists a vast amount of literature and test data that is continually growing with each mission. Compiling the observations of dynamic behavior acquired from various test geometries, environments, and techniques, as well as the proposed explanations to the observed trends, sheds light on the validity of the proposed physical mechanisms. This in turn guides future efforts to improve the experimental and computational prediction techniques and further the fundamental understanding of blunt body dynamic stability.
  • Thumbnail Image
    Item
    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.
  • Thumbnail Image
    Item
    Performance 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.