Αντικείμενο της παρούσας διδακτορικής διατριβής αποτελεί η θεωρητική και υπολογιστική προσομοίωση της πτήσης ατμοσφαιρικής καθόδου υψηλών ταχυτήτων, με ιδιαίτερη έμφαση στις υπερυπερηχητικές ταχύτητες και την αεροδυναμική και θερμοδυναμική ανάλυσή της. Η μεθοδολογία που ακολουθείται έχει ως κύριο σκοπό την πρόβλεψη του ίχνους επιστροφής υπερυπερηχητικών οχημάτων στη Γη, με δεδομένο οι ταχύτητες πτήσης να φτάνουν τα 15000 m/s (αριθμός Mach ~ 40) και οι θερμοκρασίες ανακοπής τους 15000 Κ. Στην εργασία αυτή ακολουθείται μεθοδολογική προσέγγιση και συστηματική βιβλιογραφική έρευνα στον επιστημονικοτεχνικό τομέα της αεροδυναμικής υπερθέρμανσης, που υφίστανται Υπερυπερηχητικά Οχήματα (Υ/Ο), κατά την πτήση τους στην ατμόσφαιρα. Η ανάλυση της υπερυπερηχητικής ροής, των θερμικών φορτίων και οι μέθοδοι θερμοθωράκισης των Υ/Ο αναπτύσσονται τις τελευταίες δεκαετίες και εξελίσσονται συνεχώς, αλλά μέχρι και σήμερα (2008), προκύπτουν αστοχίες, κυρίως κατά την επανείσοδό τους στην ατμόσφαιρα από το διάστημα. Για την προσομοίωση της υπερυπερηχητικής πτήσης καθόδου στην ατμόσφαιρα γίνεται μελέτη και ανάλυση των θερμοχημικών ιδιοτήτων και παραμέτρων, οι οποίες χαρακτηρίζουν τα ροϊκά πεδία στις υψηλές ταχύτητες και υψηλές θερμοκρασίες. Ο προσδιορισμός των μεταβαλλόμενων ροϊκών συνθηκών, των θερμοδυναμικών ιδιοτήτων και μεγεθών μεταφοράς θα συμβάλλει στις θεωρίες μοντελοποίησης και υπολογισμού της υψηλής θερμικής καταπόνησης, της σύστασης του υπέρθερμου αέρα και της υψηλής θερμοκρασίας του στην εξωτερική επιφάνεια του θερμομονωτικού τοιχώματος οχημάτων υψηλών ταχυτήτων, κατά την πτήση τους στην ατμόσφαιρα της Γης. Στα πλαίσια αυτά αναπτύσσονται υπολογιστικοί αλγόριθμοι προσομοίωσης και επιτυχούς πρόβλεψης του ατμοσφαιρικού ίχνους καθόδου οχημάτων υπερυπερηχητικής μεταφοράς. Τα βασικά αεροδυναμικά χαρακτηριστικά των ανωστικών οχημάτων στις υψηλές ταχύτητες υπολογίζονται με κατάλληλη προσαρμογή της κλασσικής Νευτώνειας Ροής στις υψηλές ταχύτητες και επιβεβαιώνονται με πειραματικά δεδομένα αεροδυναμικών μετρήσεων σε αεροσήραγγες υψηλών ταχυτήτων της NASA. Επιπλέον στη διατριβή ενσωματώνονται μοντέλα προσομοίωσης των ιδιοτήτων συμπεριφοράς του υπέρθερμου αέρα ως πραγματικού αερίου σε συνθήκες θερμοδυναμικής ισορροπίας σε ακραίες ροϊκές συνθήκες (υψηλές ταχύτητες, υψηλές πιέσεις και χαμηλές πυκνότητες). Πιο συγκεκριμένα γίνεται ανάλυση της μεταβαλλόμενης σύστασης και των ιδιοτήτων του αέρα (θερμοδυναμικά μεγέθη και μεγέθη μεταφοράς) στις πολύ υψηλές θερμοκρασίες του υπέρθερμου ροϊκού πεδίου. Η μελέτη αυτή θα οδηγήσει στην εξαγωγή ενός νέου μοντέλου υπολογισμού της μεταφερόμενης θερμικής ροής στην περιοχή ανακοπής υπερυπερηχητικών οχημάτων, το οποίο επιβεβαιώνεται τόσο με διεθνώς αναγνωρισμένα θερμικά μοντέλα (όπως αυτό των Fay-Riddell) όσο και με υπολογιστικές προσομοιώσεις άλλων ερευνητών. Η μεθοδολογία που ακολουθείται θα αποτελέσει τη βάση για την εξαγωγή ενός νέου θεωρητικού μοντέλου υπολογισμού της θερμοκρασίας του αέρα στην επιφάνεια του θερμοθώρακα του υπερυπερηχητικού οχήματος. Η αποτελεσματικότητα της προτεινόμενης μεθοδολογίας, με το συνδυασμό κινηματικής και αεροθερμοδυναμικής ανάλυσης σε ενιαίο υπολογιστικό αλγόριθμο, αποδεικνύεται και ενισχύεται μέσω της εφαρμογής των ανωτέρω μοντέλων προσομοίωσης σε βαλλιστικό (διαστημικός θαλαμίσκος Απόλλων) και ανωστικό (Σύστημα Διαστημικής Μεταφοράς, γνωστό ως Διαστημικό Λεωφορείο Space Shuttle) υπερυπερηχητικό όχημα. Τα αποτελέσματα της προτεινόμενης μεθόδου συγκρίνονται, αξιολογούνται και πιστοποιούνται με παρόμοια από διεθνώς αναγνωρισμένα υπολογιστικά συστήματα και πειραματικά δεδομένα μετρήσεων σε υπερυπερηχητικές αεροσήραγγες οχημάτων υψηλών ταχυτήτων. Μέσα στις επόμενες δεκαετίες, η εξέλιξη των υπερυπερηχητικών συστημάτων μεταφοράς θα είναι ραγδαία και ιδιαίτερα ελκυστική από τεχνολογικής πλευράς με ελπιδοφόρα μηνύματα για "γήϊνες" μετακινήσεις με υψηλές ταχύτητες σε σύντομους χρόνους, αλλά και πιθανές μετοικήσεις ανθρώπων-αστροναυτών σε άλλους πλανήτες του ηλιακού συστήματος. Έτσι η παρούσα διδακτορική διατριβή, αξιοποιώντας τις προόδους που έχουν συντελεστεί τα τελευταία χρόνια, εκτιμάται ότι συμβάλλει ουσιαστικά στο ακόμα υπό εξέλιξη – για τα ελληνικά δεδομένα πρωτόγνωρο – επιστημονικό πεδίο της Υπερυπερηχητικής Αεροθερμοδυναμικής, και στην ανάπτυξη μεθοδολογίας για τον αεροθερμοδυναμικό σχεδιασμό υπερυπερηχητικών οχημάτων. Το προτεινόμενο σύνθετο μοντέλο κινηματικής και θερμοδυναμικής υπολογιστικής ανάλυσης και η μεθοδολογία που ακολουθείται έχει ισχύ και εφαρμογή στην πλειονότητα των περιπτώσεων των υπερυπερηχητικών πτήσεων στη γήινη και, με κατάλληλες προσαρμογές, σε οποιαδήποτε πλανητική ατμόσφαιρα. Βεβαίως, η προτεινόμενη μεθοδολογία έχει περιθώρια εξέλιξης και ανάπτυξης, προκειμένου να βελτιωθεί η απόδοσή της με την εισαγωγή και νέων στοιχείων, αλλά και να διευρυνθεί το φάσμα των δυνατών εφαρμογών της. / The object of the present doctoral thesis constitutes the theoretical and calculating simulation of high-speed atmospheric flightmotion, with particular emphasis in hypersonic speeds and aerodynamic and thermodynamic analysis. The methodology that is followed has as main aim the prediction of return flight trace of hypersonic vehicles in Earth’s ground, assuming the speeds of flight to reach the 15000 m/s (Mach number ~ 40) and stagnation temperatures the 15000 K. In this work are followed methodological approach and systematic bibliographic research in the scientific field of aerodynamic overheating that suffers Hypersonic Vehicles(H/V) at their flight in Earth’s atmosphere. The analysis of hypersonic flow, thermal loads and new methods for thermal protection systems of H/V are developed the last decades and are evolved continuously, but until today (2008) resulting failures mainly at their reentry in atmosphere from the interval. For the simulation of the atmospheric hypersonic flight motion become study and analysis of thermodynamic properties and parameters, that characterize the flow fields in high speeds and high temperatures. The determination of altered flow conditions, thermodynamic properties and transport magnitudes will contribute in the theories of modelling and high thermal strain calculations, in the constitution of overheating air and it’s high temperature determination in the external surface of heat insulation wall of high-speed vehicles at their flight in Earth’s atmosphere. In this work are developed calculating algorithms of simulation for the successful prediction of atmospheric flight motion of hypersonic transport vehicles. The basic aerodynamic characteristics of lifting vehicles in high speeds are calculated with suitable adaptation of classic Newtonian Flow in high speeds and are confirmed with experimental data of aerodynamic measurements in high speed wind-tunnels of NASA. Moreover in this thesis are incorporated models for the simulation of properties of overheating air behaviour as real gas in thermodynamic balance in extreme flow conditions (high speeds, high pressures and low densities). Particularly becomes analysis of the altered constitution and properties of air (thermodynamic magnitudes and transport magnitudes) in very high temperatures on hypersonic flow field. This study will lead to the export of a new model for the transported thermal stagnation region calculations of hypersonic vehicles, which is confirmed so much with internationally recognized thermal models (as that of Fay-Riddell) and with calculating simulations of other researchers. The methodology that is followed will constitute the base for the export of a new theoretical model for high temperature air calculations in thermal protection systems surface of hypersonic vehicles. The effectiveness of proposed methodology, with the combination kinematic and aerothermodynamics analysis in united calculating algorithm, is proved and confirmed via the application of above simulation models on ballistic (Apollo Command Module) and lifting (Space Transportation System, known as Space Shuttle) hypersonic vehicles. The results of proposed method are compared, evaluated and certified with similarly by internationally recognized calculating systems and experimental data of measurements in hypersonic wind-tunnels for high speed vehicles. In the next decades, the development of hypersonic transportation systems will be rapid and particularly attractive from technological side with hopeful messages for “earthy” transfers with high speeds in short times, but also likely persons-astronaut missions in other planets of solar system. Thus the present doctoral thesis, developing the progress that has taken place in the past few years, is appreciated that it contributes substantially in still under development - for the Greek data unusual - scientific field of Hypersonic Aerothermodynamics, and in the growth of methodology for the aerothermodynamic construction of hypersonic vehicles. The proposed complex model of kinematic and thermodynamic calculating analysis and it’s methodology that is followed have influence and application in the majority of cases of hypersonic flights in earthy and, with properly adaptations, in anyone planetary atmosphere. Of course, the proposed methodology has margins of development and growth in order to improve her efficiency with the import of also new elements and also extended the spectrum of her possible applications.

A combined experimental and numerical study of multidimensional viscous flows at speeds exceeding 8 km/s is reported. Experiments were performed in the X3 superorbital expansion tube with air and nitrogen test flows at a Mach number and total enthalpy of 10 and 40 MJ/kg, respectively. Laminar skin friction, heat flux and pressure measurements were obtained at regular intervals along one wall of a rectangular duct. The spatial resolution of the transducers was chosen to capture the multidimensional flow phenomena within the duct. Quasi-steady flow periods were established along the entire length of the duct in the test times offered by the expansion tube. Direct skin friction measurements were accomplished through the use of ‘in house’ acceleration compensated transducers. The successful operation of these skin friction transducers in a high performance expansion tube was demonstrated. Furthermore, the systematic uncertainty in measured shear stress was significantly reduced with the development of a new pressure calibration technique. For the conditions tested, Reynolds analogy was shown to be valid to within experimental uncertainty. The experimental data was in excellent agreement with numerical estimates. Three-dimensional numerical simulations of the diverging duct revealed that the flowfield structure in the vicinity of the corners differs from that of an unbounded corner or a constant area duct. Real gas effects other than those present in the residual nonequilibrium levels of freestream dissociation were negligible for the conditions tested. A computational study of two waverider configurations recently tested in the X3 superorbital expansion tube was conducted to assist in the interpretation of past results. The off-design aerodynamic performance was also analyzed and showed that blunting the leading edges dramatically degraded the performance by increasing drag and decreasing lift for the conditions considered.

A combined experimental and numerical study of multidimensional viscous flows at speeds exceeding 8 km/s is reported. Experiments were performed in the X3 superorbital expansion tube with air and nitrogen test flows at a Mach number and total enthalpy of 10 and 40 MJ/kg, respectively. Laminar skin friction, heat flux and pressure measurements were obtained at regular intervals along one wall of a rectangular duct. The spatial resolution of the transducers was chosen to capture the multidimensional flow phenomena within the duct. Quasi-steady flow periods were established along the entire length of the duct in the test times offered by the expansion tube. Direct skin friction measurements were accomplished through the use of ‘in house’ acceleration compensated transducers. The successful operation of these skin friction transducers in a high performance expansion tube was demonstrated. Furthermore, the systematic uncertainty in measured shear stress was significantly reduced with the development of a new pressure calibration technique. For the conditions tested, Reynolds analogy was shown to be valid to within experimental uncertainty. The experimental data was in excellent agreement with numerical estimates. Three-dimensional numerical simulations of the diverging duct revealed that the flowfield structure in the vicinity of the corners differs from that of an unbounded corner or a constant area duct. Real gas effects other than those present in the residual nonequilibrium levels of freestream dissociation were negligible for the conditions tested. A computational study of two waverider configurations recently tested in the X3 superorbital expansion tube was conducted to assist in the interpretation of past results. The off-design aerodynamic performance was also analyzed and showed that blunting the leading edges dramatically degraded the performance by increasing drag and decreasing lift for the conditions considered.

A combined experimental and numerical study of multidimensional viscous flows at speeds exceeding 8 km/s is reported. Experiments were performed in the X3 superorbital expansion tube with air and nitrogen test flows at a Mach number and total enthalpy of 10 and 40 MJ/kg, respectively. Laminar skin friction, heat flux and pressure measurements were obtained at regular intervals along one wall of a rectangular duct. The spatial resolution of the transducers was chosen to capture the multidimensional flow phenomena within the duct. Quasi-steady flow periods were established along the entire length of the duct in the test times offered by the expansion tube. Direct skin friction measurements were accomplished through the use of ‘in house’ acceleration compensated transducers. The successful operation of these skin friction transducers in a high performance expansion tube was demonstrated. Furthermore, the systematic uncertainty in measured shear stress was significantly reduced with the development of a new pressure calibration technique. For the conditions tested, Reynolds analogy was shown to be valid to within experimental uncertainty. The experimental data was in excellent agreement with numerical estimates. Three-dimensional numerical simulations of the diverging duct revealed that the flowfield structure in the vicinity of the corners differs from that of an unbounded corner or a constant area duct. Real gas effects other than those present in the residual nonequilibrium levels of freestream dissociation were negligible for the conditions tested. A computational study of two waverider configurations recently tested in the X3 superorbital expansion tube was conducted to assist in the interpretation of past results. The off-design aerodynamic performance was also analyzed and showed that blunting the leading edges dramatically degraded the performance by increasing drag and decreasing lift for the conditions considered.

A combined experimental and numerical study of multidimensional viscous flows at speeds exceeding 8 km/s is reported. Experiments were performed in the X3 superorbital expansion tube with air and nitrogen test flows at a Mach number and total enthalpy of 10 and 40 MJ/kg, respectively. Laminar skin friction, heat flux and pressure measurements were obtained at regular intervals along one wall of a rectangular duct. The spatial resolution of the transducers was chosen to capture the multidimensional flow phenomena within the duct. Quasi-steady flow periods were established along the entire length of the duct in the test times offered by the expansion tube. Direct skin friction measurements were accomplished through the use of ‘in house’ acceleration compensated transducers. The successful operation of these skin friction transducers in a high performance expansion tube was demonstrated. Furthermore, the systematic uncertainty in measured shear stress was significantly reduced with the development of a new pressure calibration technique. For the conditions tested, Reynolds analogy was shown to be valid to within experimental uncertainty. The experimental data was in excellent agreement with numerical estimates. Three-dimensional numerical simulations of the diverging duct revealed that the flowfield structure in the vicinity of the corners differs from that of an unbounded corner or a constant area duct. Real gas effects other than those present in the residual nonequilibrium levels of freestream dissociation were negligible for the conditions tested. A computational study of two waverider configurations recently tested in the X3 superorbital expansion tube was conducted to assist in the interpretation of past results. The off-design aerodynamic performance was also analyzed and showed that blunting the leading edges dramatically degraded the performance by increasing drag and decreasing lift for the conditions considered.

Abstract Impact cratering is a fundamental geomorphic process on planetary surfaces. More than 60% of known hypervelocity impact craters on Earth are either partially or completely buried beneath post-impact sediments and one-third have been discovered with geophysical methods. In this thesis, geophysical surveys (gravity, magnetics, seismic, bathymetric mapping) were conducted at the deeply buried (>400 m) Holleford impact crater (~2.35 km) and two probable impact structures (Charity Shoal, Skeleton Lake) in southern Ontario, Canada. 3-D potential field models were constructed to determine the subsurface geology and buried crater morphology, and to evaluate evidence for possible impact versus endogenic origins. Holleford Crater is a deeply buried, Late Proterozoic-Early Cambrian (ca. 550 ±100 Ma) simple impact crater (~2.4 km) in southeastern Ontario, Canada. Land-based magnetic and gravity surveys and modelling were conducted in this study, recorded a ~ -3 mGal Bouguer anomaly and small (~30 nT) magnetic anomaly over the crater basin. 3-D gravity modelling revealed a deeply buried simple impact basin in Mesoproterozoic basement with an estimated rim-to-rim diameter (D) of 1.8-2 km, a residual rim height of ~20-30 m and true depth (dt) >400 m. The southeast crater rim is dissected by a 150 m deep, 400 m wide erosional channel produced by fluvial rim dissection. The outflow is infilled by >50 m of Late Cambrian clastic sediments, indicating a probable Late Proterozoic to Early Paleozoic impact event. Charity Shoal is a 1.2-km-diameter, 20 m deep, circular bedrock shoal in eastern Lake Ontario. Marine seismic profiling and total field magnetic surveys (140-line km) were conducted over a 9-km2 area and combined with available multi-beam bathymetric data to evaluate the subsurface geology and structure origin. Seismic surveys revealed ~30 m of Quaternary sediments overlying Middle Ordovician (Trenton Group) carbonates in the central basin and evidence for folding and faulting of the structure rim. Magnetic surveys recorded an annular magnetic high (> 600 nT) and a central magnetic low (~500-600 nT) coincident with a ~-1.7 mGal Bouguer gravity anomaly. The continuity of Middle Ordovician bedrock below the structure rules out a post-Paleozoic intrusion and a pre-Paleozoic intrusion is ruled out with the gravity anomaly. A deeply-buried (> 450 m) impact crater is the only scenario consistent with geophysical evidence. The crater has a rim-to-rim diameter of ~1.2 km, and rim height of ~15-20 m. A 100-m wide breach in the southwestern rim records a possible outflow channel. Skeleton Lake is a suspected (~4.0 km) Paleozoic-age impact structure in Muskoka, Ontario. The lakebed morphology, subsurface structure and possible impact origin were investigated with high-resolution geophysical surveys (magnetics, bathymetry; ~140 line-km) and 3-D magnetic modelling. Bathymetric data reveal a deep (>65 m) central basin with arcuate (Paleozoic?) bedrock ridges that rise >30 m above the southwestern lakebed. Magnetic surveys recorded a >700 nT magnetic low, which truncates northwest-southeast regional magnetic trends. Low-amplitude, northwest-trending magnetic lineaments delineate basement shear zones below the basin centre. Through-going magnetic lineaments and lack of thermal alteration (e.g., dikes, fenitization) in Mesoproterozoic rocks indicate a volcanic origin is unlikely. A 1.2 km diameter volcanic plug with an Early Cambrian remanence (D = 82.2°, I = 82.7°) can reproduce some aspects of the magnetic anomaly but is at odds with the Bouguer gravity anomaly (~ -3 mGal). Forward modelling of a crater-form basin with induction and remanence magnetization yielded an estimated structure depth of ~1200 m. The basement surface model shows a complex basement topography with no apparent rim structure and elevated ‘pinnacles’ that may represent eroded remnants of a central uplift or a highly-dissected basement topography. The structure apparent diameter (> 4.2 km) and complex basement topography suggest a heavily-modified transitional crater, similar with the Gow (Saskatchewan, Canada) and Kärdla (Estonia) impact structures. This thesis demonstrates the subsurface exploration of confirmed and suspected impact structures, integrating seismic, potential field (magnetics, gravity) and digital elevation data within a 3-D geophysical modelling workflow. The approach provides important new insights into the surface and subsurface geology, morphology, and post-emplacement modification of the Holleford impact crater, and new geophysical constraints for evaluating two suspected impact structures. Geophysical data confirm that Charity Shoal and Skeleton Lake are deep-seated, crater-form depressions in Mesoproterozoic basement rocks. The weight of geophysical and geological evidence points to impact cratering processes as opposed to an endogenic (volcanic) origin for both structures. / Thesis / Doctor of Science (PhD)

Collision with orbital debris poses a serious threat to spacecraft and astronauts. Hypervelocity impacts resulting from collisions mean that objects with a mass less than 1g can cause mission-ending damage to spacecraft. A means of shielding spacecraft against collisions is necessary. A means of testing candidate shielding methods for their efficacy in mitigating hypervelocity impacts is therefore also necessary. Cal Poly’s Electromagnetic Railgun was designed with the goal of creating a laboratory system capable of simulating hypervelocity (≥ 3 km/s) impacts. Due to several factors, the system was not previously capable of high-velocity (≥ 1 km/s) tests. A deficient projectile design is revised, and a new design is tested. The new projectile design is demonstrated to enable far greater performance than the previous design, with a muzzle velocity ≥ 1 km/sbeing verified during testing, and an energy conversion efficiency of 2.7%. A method of improving contact and controlling wear at the projectile/rail interface using silver plating and conductive silver paste is validated. A mechanism explaining the problem of internal arcing within the railgun barrel is proposed, and design recommendations are made to eliminate arcing on the basis of the work done during testing. The primary structural members are found to be deficient for their application and a failure analysis of a failed member, loading analysis of the railgun barrel, and design of new structures is undertaken and presented.