Development of an In-Flight Non-Intrusive Mass Capture System

Barhorst, Todd; Williams, Skip; Chen, Shin-Juh; Paige, M. E.; Silver, Joel A.; Sappey, Andrew D.; McCormick, Patrick J.; Masterson, Pat; Zhao, Qingchun; Sutherland, Lee; Smith, I. S.; VanHoudt, P; Hannam, J; Owenby, D

doi:10.2514/6.2009-5067

Cited by 20 publications

(5 citation statements)

References 6 publications

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“…The viability of TDLAS as a simple, low-power, robust diagnostic for scramjets has been demonstrated in several ground tests (for example [8][9][10][11]) and in one flight test [12,13]. With the notable exception of the flight test system, most tests have concentrated on water vapor measurements in the combustor.…”

Section: Previous Tunable Diode Laser Absorption Spectroscopy Senmentioning

confidence: 99%

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

et al. 2016

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The design and testing of a gas temperature and velocity scramjet engine inlet sensor based on tunable diode laser absorption spectroscopy of oxygen is discussed. The robustness and stability of the optical design necessitated by the dynamic vibrational and thermal environment were balanced against the need for compact size and very high signalto-noise ratio in a low-pressure, high-altitude flight regime. Test results demonstrated very good mechanical and thermal stability and an adequate signal-to-noise ratio for altitudes up to 30 km with predicted O 2 absorbance peaks greater than the signal standard deviation by a factor of more than 3. Nomenclature I, I 0 = signal intensity with and without sample gas (arbitrary units) T= I∕I 0 , sample gas transmittance

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Section: Previous Tunable Diode Laser Absorption Spectroscopy Senmentioning

confidence: 99%

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

et al. 2016

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“…Two purge ports are located on top of the sensor for nitrogen gas flows to prevent water condensation during wet days as the instrument is shipped to launch site or awaiting launch. A companion paper [14] discusses the development of flight vehicle, duct assembly, and optical assembly within the duct.…”

Section: Optical Mass Capture Flight Sensormentioning

confidence: 99%

Laser-Based Mass Flow Rate Sensor Onboard HFiRE Flight 1

Chen¹,

Paige²,

Silver³

et al. 2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…This approach decreases the developmental burden for each individual flight and allows the focus of each test to remain on the basic research with a series of flight tests designed "to explore fundamental hypersonic flow characteristics, hypersonic vehicle aerodynamics, and supersonic combustion performance". 3 Application of CFD in a predictive capacity to real world flight vehicles has become commonplace. However, substantial challenges remain in specifying models that can properly reproduce complex phenomena and in developing numerical methods to solve these governing equations while efficiently utilizing distributed computational resources.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of the HIFiRE-2 Scramjet Flowpath

Yentsch

Gaitonde

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Three dimensional turbulent simulations with combustion modeling are employed to understand fundamental phenomena encountered in the HIFiRE-2 scramjet flowpath. Experimental data from the ground test campaign as well as a grid resolution study is used to validate the results of the simulations. These confirmed results are then leveraged to explain the physics of dual and scramjet-mode operation in a steady sense, including detailed examinations of shock structure, boundary layer separation, and combustion chemistry. Initial results of unsteady simulations are used to investigate the process of mode-transition, and a simplified heat release model is developed and tested. Simulations of the flight test are presented and contrasted with the ground test results to characterize the effects of the inlet on the boundary layer development and internal shock structures. Overall, agreement with ground test results is excellent, and the simulations show highly complex three dimensional structures to be present in the flow. Boundary layer separation induced shock / boundary layer interactions dominate dual-mode operation, while at higher Mach numbers a flameholding effect of the barrel shock from fuel injection is striking. The effects of the inlet are found to be of great importance to accurately model flight tests, however, the same macro-scale effects as observed in the ground test simulations are dominant.

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Development of an In-Flight Non-Intrusive Mass Capture System

Cited by 20 publications

References 6 publications

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

Rugged, Scramjet Inlet Temperature and Velocity Sensor: Design and Ground Test

Laser-Based Mass Flow Rate Sensor Onboard HFiRE Flight 1

Numerical Investigation of the HIFiRE-2 Scramjet Flowpath

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