ABSTRACT Thesis (M.S.)--North Carolina State University. Includes bibliographical references (lea... more ABSTRACT Thesis (M.S.)--North Carolina State University. Includes bibliographical references (leaves 54-57).
As the X-33 nears final construction, the analytical emphasis has been redirected from generating... more As the X-33 nears final construction, the analytical emphasis has been redirected from generating design data to mitigating flight risk. Computational simulation of the flow field surrounding deflected elevon control surfaces has been performed to verify engineering estimates of the heating levels that the canted fin must be designed to withstand. This analysis serves to reaffirm design assumptions and reduce uncertainty, thus decreasing flight risk. In previous simulations, surface heating predictions were based on the assumption of a smooth body. In reality, the body surface has both protuberances, such as steps and gaps formed between seals or tiles, and control-surface deflections that divert the flow from its nominal path. These surface irregularities and control-surface deflections trigger local fluid mechanical interactions that increase the heat transfer in some zone of influence on the surface. The thermal protection system is designed to account for these local effects by ...
The X-34 vehicle will provide the first flight demonstration under NASA's Reusable Launch Veh... more The X-34 vehicle will provide the first flight demonstration under NASA's Reusable Launch Vehicle (RLV) program of a fully reusable launch vehicle. Under a fixed-price contract with NASA, Orbital Sciences Corporation (OSC) i s to provide a Mach 8 suborbital RLV technology demonstrator. The vehicle i s 18.3 meters in length, has a wingspan of 8.4 meters, and is powered by a single LOX-kerosene engine. The X-34 i s carried below an L-101 1 aircraft to an altitude in excess of 9 kilometers, where the vehicles separate, the X-34 engine starts, and the X-34 vehicle continues along its flight trajectory. The first flight is scheduled for 1999. Under a cooperative agreement with OSC, Ames Research Center was given the responsibility for designing, analyzing, and fabricating the thermal protection system (TPS) of the X-34 nosecap, wing leading edges, and rudder leading edge. Temperature, pressure, and heating rates on the surface of the X-34 were computed at six points along the X I 004...
36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
The thermal protection system on the windward side of the Lockheed-Martin X-33 technology demonst... more The thermal protection system on the windward side of the Lockheed-Martin X-33 technology demonstrator vehicle consists largely of metallic panels. As the vehicle travels through the Earth's atmosphere at hypersonic speeds, thermal gradients between the top and bottom face ...
44th AIAA Aerospace Sciences Meeting and Exhibit, 2006
An instrumented aircraft and ground-based observing campaign was mounted to measure the radiation... more An instrumented aircraft and ground-based observing campaign was mounted to measure the radiation from the hypervelocity (11.0 km/s) reentry of the Genesis Sample Return Capsule prior to landing on the Utah Test and Training Range on September 08, 2004. The goal was to validate predictions of surface heating, the physical conditions in the shock layer, and the amount and nature of gaseous and solid ablation products as a function of altitude. This was the first hypervelocity reentry of a NASA spacecraft since the Apollo era. Estimates of anticipated emissions were made. Erroneous pointing instructions prevented us from acquiring spectroscopic data, but staring instruments measured broadband photometric and acoustic information. A surface-averaged brightness temperature was derived as a function of altitude. From this, we conclude that the observed optical emissions were consistent with most of the emitted light originating from a gray body continuum, but with a surface averaged temperature of 570 K less than our estimate from the predicted heat flux. Also, the surface remained warm longer than expected. We surmise that this is on account of conduction into the heat shield material, ablative cooling, and finite-rate wall catalycity. Preparations are underway to observe a second hypervelocity reentry 12.8 km/s) when the Stardust Sample Return Capsule returns to land at U.T.T.R. on January 15, 2006. Nomenclature A = projected surface area (in m 2 ) BB λ (T) = Planck curve * Mission Scientist, SETI Institute, no AIAA member † Program manager, NASA Ames Research Center, AIAA Member Associate Fellow American Institute of Aeronautics and Astronautics 1 44th AIAA Aerospace Sciences Meeting and Exhibit (Reno, Nevada. 9 -12 Jan 2006 ) c = speed of light = 2.99793 x 10 8 m/s C d = drag coefficient D = the distance to the SRC (in m) h = Planck constant = 6.62620 x 10 -34 J s k = Boltzmann's constant = 1.38062 x 10 -23 J/K λ = wavelength (m) MAC = Multi-Instrument Aircraft Campaign ρ = air density SRC = Sample Return Capsule T = temperature Introduction HE Genesis Sample-Return-Capsule (SRC) Entry Observing campaign ("Hyperseed MAC") aimed to deploy spectrographic, imaging, and infrasound instruments to derive the physical conditions during reentry of the Genesis Sample-Return-Capsule. 1 These data can be used for the evaluation of aerothermal heating and material response models, 2 shock layer radiation models, Thermal Protection System (TPS) performance, accident investigations, and for studies of the delivery of organic compounds for the origin of life by small-asteroid impacts. 3
46th AIAA Aerospace Sciences Meeting and Exhibit, 2008
At NASA Ames Research Center a novel handheld 3D sensing instrument has been developed with the c... more At NASA Ames Research Center a novel handheld 3D sensing instrument has been developed with the capability of rapidly scanning objects and creating high-resolution 3D surface maps. This technology, originally designed for the detection and measurement of defects on the Space Shuttle thermal Tiles, was modified to meet the specific task of scanning Stardust's post flight Heatshield. The end result
A new Crew Transfer Vehicle (CTV) design study that compares the changes in vehicle performance a... more A new Crew Transfer Vehicle (CTV) design study that compares the changes in vehicle performance and safety as a result of using a sharp-nosed configuration is presented. An overview of work accomplished within a one-year research study is given. The primary objective of the ...
ABSTRACT This conference features the work of authors from: Georgia Tech’s Space Systems Design L... more ABSTRACT This conference features the work of authors from: Georgia Tech’s Space Systems Design Lab, Aerospace Systems Design Lab, School of Aerospace Engineering, Georgia Tech Research Institute; NASA’s Jet Propulsion Laboratory, Marshall Space Flight Center, Goddard Space Flight Center, Langley Research Center; and other aerospace industry and academic institutions An overview of the reconstruction analyses performed for the Genesis capsule entry is described. The results indicate that the actual entry prior to the drogue deployment failure was very close to the pre-entry predictions. The capsule landed M.3 km south of the desired target at Utah Test and Training Range. Analysis on infrared video footage (obtained from the tracking stations) during the descent estimated the onset of the capsule tumble at Mach P.9. Frequency analysis on the infrared video data indicates that the aerodynamics generated for the Genesis capsule reasonably predicted the drag and static stability. Observations of the heatshield support the pre-entry simulation estimates of a small hypersonic angles-of attack, since there is very little, if any, charring of the shoulder region or the aftbody. Through this investigation, an overall assertion can be made that all the data gathered from the Genesis entry is consistent with flight performance close to the nominal pre-entry prediction. Consequently, the design principles and methodologies utilized for the flight dynamics, aerodynamics, and aerothermodynamics analyses have been corroborated. AIAA Space Systems Technical Committee ; AIAA Space Transportation Systems Technical Committee ; Space Technology Advanced Research Center
ABSTRACT The radiation emitted by the Stardust sample return capsule during reentry into Earth&am... more ABSTRACT The radiation emitted by the Stardust sample return capsule during reentry into Earth's atmosphere on 15 January 2006 was measured with a staring airborne intensified camera, equipped with an objective transmission grating. The instrumental setup was designed to provide low-resolution spectra of the capsule's radiation, even if other instruments would fail in tracking the object. Spectra were recorded at the video frame rate of 30 Hz. The spectra covered the range of 380-860 nm, with a dispersion of 2.3 nm/pixel and a full-width-at-half-maximum resolution of 7 nm. Fully calibrated results, to an absolute precision of similar to 17%, are presented for the time period from 09:57:17 to 09:57:43 Coordinated Universal Time, averaged over periods of 1 s. The data provided records of the CN band intensity detected throughout flight (unsaturated), the continuum emission (partially saturated), and the shock plasma emissions of oxygen and nitrogen during peak heating (partially saturated). A spectrum of wake radiation is also presented.
The thermal protection system on the windward side of the Lockheed Martin X-33 technology demonst... more The thermal protection system on the windward side of the Lockheed Martin X-33 technology demonstrator vehicle consists largely of metallic panels. As the vehicle travels through the Earth's atmosphere at hypersonic speeds, thermal gradients between the top and bottom face ...
... Authors: Jenniskens, P.; Jordan, D.; Kontinos, D.; Wright, M.; Olejniczak, J.; Raiche, G.; We... more ... Authors: Jenniskens, P.; Jordan, D.; Kontinos, D.; Wright, M.; Olejniczak, J.; Raiche, G.; Wercinski, P.; Schilling, E.; Taylor, M.; Rairden, R.; Stenbaek-Nielsen, H ... early in the trajectory, from the ablation of a white paint layer that had been applied to the heat shield for thermal control ...
Phenolic Impregnated Carbon Ablator (PICA) was developed at NASA Ames Research Center under the l... more Phenolic Impregnated Carbon Ablator (PICA) was developed at NASA Ames Research Center under the lightweight ceramic ablator development program in the'80s. PICA has the advantages of low density (~ 0.27 g/cc) coupled with efficient ablative capability at high ...
ABSTRACT Thesis (M.S.)--North Carolina State University. Includes bibliographical references (lea... more ABSTRACT Thesis (M.S.)--North Carolina State University. Includes bibliographical references (leaves 54-57).
As the X-33 nears final construction, the analytical emphasis has been redirected from generating... more As the X-33 nears final construction, the analytical emphasis has been redirected from generating design data to mitigating flight risk. Computational simulation of the flow field surrounding deflected elevon control surfaces has been performed to verify engineering estimates of the heating levels that the canted fin must be designed to withstand. This analysis serves to reaffirm design assumptions and reduce uncertainty, thus decreasing flight risk. In previous simulations, surface heating predictions were based on the assumption of a smooth body. In reality, the body surface has both protuberances, such as steps and gaps formed between seals or tiles, and control-surface deflections that divert the flow from its nominal path. These surface irregularities and control-surface deflections trigger local fluid mechanical interactions that increase the heat transfer in some zone of influence on the surface. The thermal protection system is designed to account for these local effects by ...
The X-34 vehicle will provide the first flight demonstration under NASA's Reusable Launch Veh... more The X-34 vehicle will provide the first flight demonstration under NASA's Reusable Launch Vehicle (RLV) program of a fully reusable launch vehicle. Under a fixed-price contract with NASA, Orbital Sciences Corporation (OSC) i s to provide a Mach 8 suborbital RLV technology demonstrator. The vehicle i s 18.3 meters in length, has a wingspan of 8.4 meters, and is powered by a single LOX-kerosene engine. The X-34 i s carried below an L-101 1 aircraft to an altitude in excess of 9 kilometers, where the vehicles separate, the X-34 engine starts, and the X-34 vehicle continues along its flight trajectory. The first flight is scheduled for 1999. Under a cooperative agreement with OSC, Ames Research Center was given the responsibility for designing, analyzing, and fabricating the thermal protection system (TPS) of the X-34 nosecap, wing leading edges, and rudder leading edge. Temperature, pressure, and heating rates on the surface of the X-34 were computed at six points along the X I 004...
36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
The thermal protection system on the windward side of the Lockheed-Martin X-33 technology demonst... more The thermal protection system on the windward side of the Lockheed-Martin X-33 technology demonstrator vehicle consists largely of metallic panels. As the vehicle travels through the Earth's atmosphere at hypersonic speeds, thermal gradients between the top and bottom face ...
44th AIAA Aerospace Sciences Meeting and Exhibit, 2006
An instrumented aircraft and ground-based observing campaign was mounted to measure the radiation... more An instrumented aircraft and ground-based observing campaign was mounted to measure the radiation from the hypervelocity (11.0 km/s) reentry of the Genesis Sample Return Capsule prior to landing on the Utah Test and Training Range on September 08, 2004. The goal was to validate predictions of surface heating, the physical conditions in the shock layer, and the amount and nature of gaseous and solid ablation products as a function of altitude. This was the first hypervelocity reentry of a NASA spacecraft since the Apollo era. Estimates of anticipated emissions were made. Erroneous pointing instructions prevented us from acquiring spectroscopic data, but staring instruments measured broadband photometric and acoustic information. A surface-averaged brightness temperature was derived as a function of altitude. From this, we conclude that the observed optical emissions were consistent with most of the emitted light originating from a gray body continuum, but with a surface averaged temperature of 570 K less than our estimate from the predicted heat flux. Also, the surface remained warm longer than expected. We surmise that this is on account of conduction into the heat shield material, ablative cooling, and finite-rate wall catalycity. Preparations are underway to observe a second hypervelocity reentry 12.8 km/s) when the Stardust Sample Return Capsule returns to land at U.T.T.R. on January 15, 2006. Nomenclature A = projected surface area (in m 2 ) BB λ (T) = Planck curve * Mission Scientist, SETI Institute, no AIAA member † Program manager, NASA Ames Research Center, AIAA Member Associate Fellow American Institute of Aeronautics and Astronautics 1 44th AIAA Aerospace Sciences Meeting and Exhibit (Reno, Nevada. 9 -12 Jan 2006 ) c = speed of light = 2.99793 x 10 8 m/s C d = drag coefficient D = the distance to the SRC (in m) h = Planck constant = 6.62620 x 10 -34 J s k = Boltzmann's constant = 1.38062 x 10 -23 J/K λ = wavelength (m) MAC = Multi-Instrument Aircraft Campaign ρ = air density SRC = Sample Return Capsule T = temperature Introduction HE Genesis Sample-Return-Capsule (SRC) Entry Observing campaign ("Hyperseed MAC") aimed to deploy spectrographic, imaging, and infrasound instruments to derive the physical conditions during reentry of the Genesis Sample-Return-Capsule. 1 These data can be used for the evaluation of aerothermal heating and material response models, 2 shock layer radiation models, Thermal Protection System (TPS) performance, accident investigations, and for studies of the delivery of organic compounds for the origin of life by small-asteroid impacts. 3
46th AIAA Aerospace Sciences Meeting and Exhibit, 2008
At NASA Ames Research Center a novel handheld 3D sensing instrument has been developed with the c... more At NASA Ames Research Center a novel handheld 3D sensing instrument has been developed with the capability of rapidly scanning objects and creating high-resolution 3D surface maps. This technology, originally designed for the detection and measurement of defects on the Space Shuttle thermal Tiles, was modified to meet the specific task of scanning Stardust's post flight Heatshield. The end result
A new Crew Transfer Vehicle (CTV) design study that compares the changes in vehicle performance a... more A new Crew Transfer Vehicle (CTV) design study that compares the changes in vehicle performance and safety as a result of using a sharp-nosed configuration is presented. An overview of work accomplished within a one-year research study is given. The primary objective of the ...
ABSTRACT This conference features the work of authors from: Georgia Tech’s Space Systems Design L... more ABSTRACT This conference features the work of authors from: Georgia Tech’s Space Systems Design Lab, Aerospace Systems Design Lab, School of Aerospace Engineering, Georgia Tech Research Institute; NASA’s Jet Propulsion Laboratory, Marshall Space Flight Center, Goddard Space Flight Center, Langley Research Center; and other aerospace industry and academic institutions An overview of the reconstruction analyses performed for the Genesis capsule entry is described. The results indicate that the actual entry prior to the drogue deployment failure was very close to the pre-entry predictions. The capsule landed M.3 km south of the desired target at Utah Test and Training Range. Analysis on infrared video footage (obtained from the tracking stations) during the descent estimated the onset of the capsule tumble at Mach P.9. Frequency analysis on the infrared video data indicates that the aerodynamics generated for the Genesis capsule reasonably predicted the drag and static stability. Observations of the heatshield support the pre-entry simulation estimates of a small hypersonic angles-of attack, since there is very little, if any, charring of the shoulder region or the aftbody. Through this investigation, an overall assertion can be made that all the data gathered from the Genesis entry is consistent with flight performance close to the nominal pre-entry prediction. Consequently, the design principles and methodologies utilized for the flight dynamics, aerodynamics, and aerothermodynamics analyses have been corroborated. AIAA Space Systems Technical Committee ; AIAA Space Transportation Systems Technical Committee ; Space Technology Advanced Research Center
ABSTRACT The radiation emitted by the Stardust sample return capsule during reentry into Earth&am... more ABSTRACT The radiation emitted by the Stardust sample return capsule during reentry into Earth's atmosphere on 15 January 2006 was measured with a staring airborne intensified camera, equipped with an objective transmission grating. The instrumental setup was designed to provide low-resolution spectra of the capsule's radiation, even if other instruments would fail in tracking the object. Spectra were recorded at the video frame rate of 30 Hz. The spectra covered the range of 380-860 nm, with a dispersion of 2.3 nm/pixel and a full-width-at-half-maximum resolution of 7 nm. Fully calibrated results, to an absolute precision of similar to 17%, are presented for the time period from 09:57:17 to 09:57:43 Coordinated Universal Time, averaged over periods of 1 s. The data provided records of the CN band intensity detected throughout flight (unsaturated), the continuum emission (partially saturated), and the shock plasma emissions of oxygen and nitrogen during peak heating (partially saturated). A spectrum of wake radiation is also presented.
The thermal protection system on the windward side of the Lockheed Martin X-33 technology demonst... more The thermal protection system on the windward side of the Lockheed Martin X-33 technology demonstrator vehicle consists largely of metallic panels. As the vehicle travels through the Earth's atmosphere at hypersonic speeds, thermal gradients between the top and bottom face ...
... Authors: Jenniskens, P.; Jordan, D.; Kontinos, D.; Wright, M.; Olejniczak, J.; Raiche, G.; We... more ... Authors: Jenniskens, P.; Jordan, D.; Kontinos, D.; Wright, M.; Olejniczak, J.; Raiche, G.; Wercinski, P.; Schilling, E.; Taylor, M.; Rairden, R.; Stenbaek-Nielsen, H ... early in the trajectory, from the ablation of a white paint layer that had been applied to the heat shield for thermal control ...
Phenolic Impregnated Carbon Ablator (PICA) was developed at NASA Ames Research Center under the l... more Phenolic Impregnated Carbon Ablator (PICA) was developed at NASA Ames Research Center under the lightweight ceramic ablator development program in the'80s. PICA has the advantages of low density (~ 0.27 g/cc) coupled with efficient ablative capability at high ...
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