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Tunable diode laser absorption spectroscopy using an external cavity diode laser operating in the infra-red has been developed to monitor CO2 in the freestream of the Longshot hypervelocity facility at the Von Karman Institute for Fluid Dynamics. The Longshot facility offers a unique European facility for ground testing and numerical validation applications, however, some of the traditional data rebuilding aspects are in question. A non-intrusive absorption sensor could significantly aid in improving the knowledge of freestream static values thereby improving the models used in data rebuilding and numerical simulation. The design of such a sensor also expands the spectroscopic capabilities of the Von Karman Institute. The absorption sensor is designed around the single P12 (00001)-(30013) rovibrational transition near 1.6µm (6218.09cm-1 specifically) which yields relatively weak direct absorption levels at about 3.5% per meter for typical Longshot freestream conditions. However, when handled carefully, adequate signal-to-noise can be acquired to exploit significant flow information. By being able to operate in this range, total sensor cost can be easily an a factor of two or more cheaper than sensors designed for the deeper infrared. All sensor elements were mounted to a compact portable optics bench utilizing single-mode optical fibers to allow for quick installation at different facilities by eliminating tedious optical realigning. Scans at 600Hz were performed over 20ms of the 40ms test time to extract core static temperature, pressure and velocity. These results are compared with the current state of the Longshot data rebuild method. The non-uniform flow properties of the shear layer and test cabin rested gas accumulation was of an initial concern. The temperature and density gradients along with significant radial velocity components could result in DLAS temperature, pressure and velocity that are significantly different than that of the target freestream inviscid core values. Fortunately, with the proper selection of the P12 rotational number, this effect could be more or less ignored as the higher temperature and lower density gas of this region is relatively transparent. Ultimately, acquired temperature and density were moderately accurate when compared to Longshot rebuilt results owing primarily to the baseline extraction which poses issues for such low absorption signals. However, the extracted velocity data are quite accurate. This is a definite puls for the sensor as the freestream enthalpy of cold hypersonic facilities is dictated primarily by the kinetic energy contribution. Being able to compare velocity gives insight to the level of vibration non-equilibrium in the flow. The velocity of the DLAS and the Longshot rebuild are quite close. This adds more weight to the argument that vibrational excitation is very low (if present at all) in the free stream and that the van de derWaals equation of state usage and constant specific heat assumption might be an adequate model for the data rebuild after all.

ITC/USA 2009 Conference Proceedings / The Forty-Fifth Annual International Telemetering Conference and Technical Exhibition / October 26-29, 2009 / Riviera Hotel & Convention Center, Las Vegas, Nevada / The Weapons System Test and Integration Laboratory (WSTIL) at the U.S. Army Yuma Proving Ground (YPG) will provide a new capability for ground based testing in this arena. Current and near term YPG scheduled test programs will benefit tremendously from this enhanced ground test capability provided by the Weapons STIL. The Weapons STIL's design goals center on the implementation of an automated mechanism for testing the weapon systems and sensors that are currently the responsibility of the YPG facility. To meet the Army's weapons test needs the Weapons STIL incorporates various levels of digital stimulation, human-in-the-loop, hardware-in-the-loop, and installed system test facility (ISTF) techniques to maximize ground testing in order to focus and optimize subsequent open air flight testing. This paper describes this work in progress.

L’exploration des quatre planètes géantes gazeuses, Jupiter, Saturne, Neptune et Uranus, est importante pour comprendre l’évolution de notre système solaire et plus généralement de l’univers. Les sondes entrant dans l’atmosphère des géantes gazeuses ont des vitesses de 20 à 50 km/s, largement supérieures aux vitesses d’entrée atmosphérique sur les autres planètes du système solaire. Il s’agit d’un problème complexe car les conditions d’entrées sont brutales et les vitesses associées dépassent largement les capacités des installations d’essai au sol actuelles. Cette thèse examine la possibilité de simuler expérimentalement les conditions d’entrées proposées pour Uranus et Saturne à 22.3 et 26.9 km/s avec un tube d’expansion à piston libre. D’abord, la possibilité de simuler les conditions directement en recréant la vitesse d’entrée réelle a été étudiée. Il a été trouvé qu’il était possible de simuler l’entrée d’Uranus mais seulement avec de grandes incertitudes. Pour cette raison, il a été proposé d’utiliser une substitution du gaz d’essai établie, dans lequel soit le pourcentage d’hélium dans l’atmosphère H2/He est augmenté, soit l’hélium est remplacé par du néon, un gaz noble plus lourd. Cela permet de simuler uniquement les conditions postchoc des entrées. Théoriquement, il a été constaté que ces substitutions permettaient de simuler l’entrée Uranus ou Saturne, ce qui a été confirmé expérimentalement à l’aide d’hélium. Notant l’intérêt actuel d’envoyer des sondes d’entrée atmosphérique vers ces deux planètes, cette étude a démontré que les capacités expérimentales requises sont disponibles pour la réalisation d’expériences simulées avec les modèles d’essais. / Exploration of the four gas giant planets, Jupiter, Saturn, Uranus, and Neptune, is important for understanding the evolution of both our solar system and the greater universe. Due to their size, flight into the gas giants involves atmospheric entry velocities between 20 and 50 km/s. This is a complex issue because the entry conditions are harsh but the related velocities are mostly beyond the capabilities of current ground testing facilities. As such, this thesis examines the possibility of experimentally simulating proposed Uranus and Saturn entries at 22.3 and 26.9 km/s in a free piston driven expansion tube, the most powerful type of impulse wind tunnel. Initially, the possibility of simulating the conditions directly by re-creating the true flight velocity was investigated. It was found to be possible to simulate the 22.3 km/s Uranus entry, but not without large uncertainties in the test condition. For this reason, it was proposed to use an established test gas substitition where the percentage of helium in the H2/He atmosphere is increased, or the helium is substituted for the heavier noble gas neon. This allows just the post-shock conditions of the entries to be simulated. Theoretically it was found that these substitutions allowed both Uranus or Saturn entry to be simulated, which was confirmed experimentally using helium. Noting the current interest in sending atmospheric entry probes to both of these planets, this study has demonstrated that the required experimental capabilities are available for performing simulated experiments using test models.

Tunable diode laser absorption spectroscopy using an external cavity diode laser operating in the infra-red has been developed to monitor CO2 in the freestream of the Longshot hypervelocity facility at the Von Karman Institute for Fluid Dynamics. The Longshot facility offers a unique European facility for ground testing and numerical validation applications, however, some of the traditional data rebuilding aspects are in question. A non-intrusive absorption<p>sensor could significantly aid in improving the knowledge of freestream static values thereby improving the models used in data rebuilding and numerical simulation. The design of such a sensor also expands the spectroscopic capabilities of the Von Karman Institute.<p><p>The absorption sensor is designed around the single P12 (00001)-(30013) rovibrational transition near 1.6µm (6218.09cm-1 specifically) which yields relatively weak direct absorption levels at about 3.5% per meter for typical Longshot freestream conditions. However, when handled carefully, adequate signal-to-noise can be acquired to exploit significant flow information. By being able to operate in this range, total sensor cost can be easily an a factor of two or more cheaper than sensors designed for the deeper infrared. All sensor elements were mounted to a compact portable optics bench utilizing single-mode optical fibers to allow for quick installation at different facilities by eliminating tedious optical realigning. Scans at 600Hz were performed over 20ms of the 40ms test time to extract core static temperature, pressure and velocity.<p><p>These results are compared with the current state of the Longshot data rebuild method. The non-uniform flow properties of the shear layer and test cabin rested gas accumulation was of an initial concern. The temperature and density gradients along with significant radial velocity components could result in DLAS temperature, pressure and velocity that are significantly different than that of the target freestream inviscid core values. Fortunately, with the proper selection of the P12 rotational number, this effect could be more or less ignored as the higher temperature and lower density gas of this region is relatively transparent.<p><p>Ultimately, acquired temperature and density were moderately accurate when compared to Longshot rebuilt results owing primarily to the baseline extraction which poses issues for such low absorption signals. However, the extracted velocity data are quite accurate. This is a definite puls for the sensor as the freestream enthalpy of cold hypersonic facilities is dictated primarily by the kinetic energy contribution. Being able to compare velocity gives insight to the level of vibration non-equilibrium in the flow. The velocity of the DLAS and the Longshot rebuild are quite close. This adds more weight to the argument that vibrational excitation is very low (if present at all) in the free stream and that the van de derWaals equation of state usage and constant specific heat assumption might be an adequate model for the data rebuild after all. / Doctorat en Sciences de l'ingénieur / info:eu-repo/semantics/nonPublished

<p>Air intakes are a fundamental part of all high speed airbreathing propulsion concepts. The main purpose of an intake is to capture and compress freestream air for the engine. At hypersonic speeds, the intake’s surface and shock structure effectively slow the airflow through ram-air compression. In supersonic-combustion ramjets, the captured airflow remains supersonic and generates complicated shock structures. The design of these systems require careful evaluation of proposed operating conditions and relevant aerodynamic phenomena. The physics of these systems, such as the intake’s operability range, mass capture efficiency, back-pressure resiliency, and intake unstart margins are all open areas of research. </p> <p><br></p> <p>A high speed intake, dubbed the Indiana Intake Testbed, was developed for experimentation within the Boeing-AFOSR Mach 6 Quiet Tunnel at Purdue University. This inward-turning, mixed compression intake was developed from osculating axisymmetric theory and uses a streamtracing routine to create a shape-transitioned geometry. To account for boundary layer growth, a viscous correction was implemented on the intake’s compression surfaces. This comprehensive independent design code was pursued to generate an unrestricted geometry that satisfies academic inquiry into fluid dynamic interactions relevant to intakes. Additionally, the design code contains built-in analysis tools that are compared against CFD calculations and experimental data. </p> <p><br></p> <p>Two blockage models were constructed and outfitted with Kulite pressure transducers to detect possible intake start and unstart effects. Due to an error in the design code, the preliminary blockage models’ lower surfaces were oversized. The two intake models were tested over a freestream Reynolds number sweep, under noisy and quiet flow, at one non-zero angle of attack, and at a singular back-pressure condition. Back-pressure effects acted to unstart the intake and provide a comparison between forced-unstart and started states. The experimental campaign cataloged both tunnel starting and inlet starting conditions, which informed the design of the finalized model. The finalized model is presented herein. Future experiments to study isolator shock-trains, shock-wave boundary layer interactions, and possible instances of boundary layer transition on the intake’s compression surface are planned. </p>

International Telemetering Conference Proceedings / October 17-20, 1994 / Town & Country Hotel and Conference Center, San Diego, California / Since the Gulf War, there has been significant interest in Theater Missile Defense (TMD) resulting in funding growth from tens of millions of dollars at the time of the Gulf War to $1.7 Billion in 1994. The Ballistic Missile Defense Organization (BMDO) has developed a Theater Missile Defense test and evaluation program that will assess technological feasibility and the degree to which system functionality and performance meet technical and operational requirements. The complexity of the TMD program necessitates a comprehensive test program which includes flight testing, ground testing, and modeling and simulation. This article will provide and overview the requirements and capabilities needed to satisfy these requirements. The data processing, and telemetry communities will play a major role in providing the expertise to support the development of the nation’s future Theater Missile Defense capabilities.