Low cost surface regression sensor for hybrid fuels, solid propellants, and ablatives

Gramer, Daniel; Taagen, Thomas

doi:10.2514/6.2001-3529

Cited by 5 publications

(11 citation statements)

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“…At least two different resistance-based regression measurement technologies have been implemented [25,26]. These sensors are designed to be embedded in the material of interest and regress along with it.…”

Section: A Principle Of Methodsmentioning

confidence: 99%

“…Two general sensor installation approaches have been successfully demonstrated [26]. Two general sensor installation approaches have been successfully demonstrated [26].…”

Section: Mirras Installationmentioning

confidence: 99%

“…These two approaches eliminate the need to produce any motor case penetrations or other modifications and are particularly well suited for flight-type motor testing or onboard flight systems [26]. Preliminary designs indicate this system would be about the size of a nickel for a MIRRAS sensor.…”

Section: Mirras Signal Conditioning and Transmissionmentioning

confidence: 99%

“…Extensive subscale MIRRAS sensor development was completed in a 25 lbf water-cooled HTPB/GOX hybrid motor [26]. These tests shaped the general sensor design and signal conditioning approach.…”

Section: Solid-fuel Applicationsmentioning

confidence: 99%

“…Limited testing of the MIRRAS sensor has also been conducted in ablative materials [26]. The top three-quarters of a hybrid motor was cast with HTPB, and two MIRRAS sensors were cast into a silicone ablative in the bottom one-quarter of the motor.…”

Section: Ablative Materials Applicationsmentioning

confidence: 99%

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Solid-Fuel Pyrolysis Phenomena and Regression Rate, Part 2: Measurement Techniques

2007

Fundamentals of Hybrid Rocket Combustion and Propulsion

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Nomenclature A= Plasma capacitance gauge area, m 2 A p = instantaneous grain port cross-sectional area, Eq. (4), cm 2 a = classical regression law constant, Eq. (1) b = curve-fit exponent C = mechanical wave velocity, m/s C = general constant, Eq. (6) dP/dt = pressure gradient, MPa/s G 0 = oxidizer mass flux, Eq. (1), kg/cm 2 · s I (θ) = x-ray intensity arriving at the input screen of the image intensifier at an angle of θ , R/s I 0 = initial x-ray intensity, R/s k = wave number k P = wave velocity variation coefficient with respect to pressure, MPa −1 k T = wave velocity variation coefficient with respect to temperature, K −1 168 F. CAUTY ET AL. L (θ) = interaction length of x ray and material, m 0 = initial thickness, m m = linear attenuation coefficient of photoelectric absorption, m −1 m 0 = oxidizer mass flow rate, Eq. (3), kg/s n = classical regression law exponent, Eq. (1) P = pressure, MPa R f = cumulative web regression at time t f , Eq. (8), cm R p = initial grain port radius at t = 0, Eq. (4), cm R t = cumulative web regression at time t, Eq. (2), cm r = instantaneous surface regression rate, Eq. (1), cm/s r b , R b = burning rate, mm/s T = temperature, K t = time, Eq. (6), s t f = elapsed time between first and last data point, s ΔC = capacitance change ε = permittivity or dielectric constant λ = wavelength, m σ P = initial temperature sensitivity of the burning rate at constant pressure, K −1 τ = propagation time, μs Subscripts φ = phase shift, deg b = burning c = cutoff G = grain P = pressure ref = reference conditions T = temperature 0 = initial conditions

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Section: A Principle Of Methodsmentioning

confidence: 99%

“…Two general sensor installation approaches have been successfully demonstrated [26]. Two general sensor installation approaches have been successfully demonstrated [26].…”

Section: Mirras Installationmentioning

confidence: 99%

Section: Mirras Signal Conditioning and Transmissionmentioning

confidence: 99%

Section: Solid-fuel Applicationsmentioning

confidence: 99%

Section: Ablative Materials Applicationsmentioning

confidence: 99%

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Solid-Fuel Pyrolysis Phenomena and Regression Rate, Part 2: Measurement Techniques

2007

Fundamentals of Hybrid Rocket Combustion and Propulsion

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Studies on EVA‐Based Wax Fuel for Launch Vehicle Applications

Kumar

Ramakrishna

2016

Propellants Explo Pyrotec

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A fuel for the hybrid rocket system was developed. The attempts made to improve the mechanical properties of wax by adding EVA (ethylene vinyl acetate) are illustrated. It was observed that the mechanical properties obtained by adding EVA to wax were dependent on the process of curing the fuel specimen. A proprietary method of curing the fuel specimen was established. The percentage elongation obtained with 20 % EVA and 80 % of wax was around 17 %, which was much higher than the values obtained with pure wax (4 %). It was observed from the study that the higher the percentage of EVA content in wax was, the better the mechanical properties were. Regression rate studies with EVA and wax combination were carried out. It was observed that the regression rate decreased upon addition of EVA in wax. This reduction was compensated by using a bluff body at the head end. The regression rate obtained with 20 % EVA and 80 % wax even with the use of bluff body is lower than that obtained with pure wax, but is around 3.5 times the regression rate obtained with polymeric fuels.

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Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy

Wang

Lin

et al. 2021

Acta Astronautica

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Low cost surface regression sensor for hybrid fuels, solid propellants, and ablatives

Cited by 5 publications

References 0 publications

Solid-Fuel Pyrolysis Phenomena and Regression Rate, Part 2: Measurement Techniques

Solid-Fuel Pyrolysis Phenomena and Regression Rate, Part 2: Measurement Techniques

Studies on EVA‐Based Wax Fuel for Launch Vehicle Applications

Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy

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