Measurement of regression rate in hybrid rocket using combustion chamber pressure

Kumar, Rajiv; Ramakrishna, P. A.

doi:10.1016/j.actaastro.2014.06.044

Cited by 28 publications

(13 citation statements)

References 34 publications

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“…Initially, the experiments were conducted without any post‐combustion chamber, similar to the experiments reported in the literature [10, 15]. It was observed that the combustion with only H 2 O 2 as oxidizer was not sustained, and the pressure‐time trace was similar to the one seen in Figure 5.…”

Section: Resultsmentioning

confidence: 75%

“…This mass of the oxidizer was divided by the burn time to obtain the average mass flow rate of the oxidizer (

{\dot{m}}_{o x, a v g}

). This method has been explained in detail by Marothiya and Ramakrishna [10] and Kumar and Ramakrishna [15]. For measuring the mass flow rate of H 2 O 2 , the orifice meter was calibrated by measuring the mass of H 2 O 2 coming out injector in a known time, and an empirical equation was determined and used for measuring the flow rate of H 2 O 2 passing through the orifice meter.…”

Section: Methodsmentioning

confidence: 99%

“…Therefore, it was decided that initially, oxygen would be used for the ignition, and H 2 O 2 would be introduced in the combustion chamber afterwards. The combustion with oxygen was initiated with a small solid-propellant similar to that described in earlier literature [10,15], and [17] emanating from the same lab. The heat generated by the reaction of fuel with O 2 would be used to decompose the H 2 O 2 in the combustion chamber.…”

Section: Developing the Propellant And Experimental Facilitymentioning

confidence: 99%

“…Mass loss of fuel was noted only for the period when the H 2 O 2 was supplied into the combustion chamber. This mass loss was used to obtain a burn rate versus mass flux plot by using the weight loss method as described by Rajiv and Ramakrishna [15,17]. The burn rates were obtained for the best performing composition in terms of specific impulse (30 % wax + 70 % Al-PTFE).…”

Section: Developing the Propellant And Experimental Facilitymentioning

confidence: 99%

See 3 more Smart Citations

Development of H₂O₂ Based Mixed Hybrid Rocket

Marothiya

Ramakrishna

Saravanan³

et al. 2021

Propellants Explo Pyrotec

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As a green oxidizer, hydrogen peroxide is an earth-storable, non-toxic liquid oxidizer. This study shows a possible combination of wax-based aluminized fuel with hydrogen peroxide as an oxidizer, which can be used to improve the specific impulse and density specific impulse of the hybrid rockets. In this study, various methods have been tried to ignite the hybrid rocket and measure the regression rates and ballistic performance. This research presents sustainable combustion of hydrogen peroxide with aluminized wax-based fuel without the need for any cata-lyst bed. This combination of hybrid propellant demonstrates superiority over other fuels with hydrogen peroxide and shows promises in terms of an option as the future green propellant. The theoretical specific impulse of about 315 s at 100 bar with a nozzle exit area ratio of 50 is shown by this fuel and oxidizer combination. Another benefit of this combination of hybrid propellant is that the peak specific impulse is obtained at an O/F ratio of almost unity which makes the system more compact.

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Section: Resultsmentioning

confidence: 75%

“…This mass of the oxidizer was divided by the burn time to obtain the average mass flow rate of the oxidizer (

{\dot{m}}_{o x, a v g}

Section: Methodsmentioning

confidence: 99%

Section: Developing the Propellant And Experimental Facilitymentioning

confidence: 99%

Section: Developing the Propellant And Experimental Facilitymentioning

confidence: 99%

See 2 more Smart Citations

Development of H₂O₂ Based Mixed Hybrid Rocket

Marothiya

Ramakrishna

Saravanan³

et al. 2021

Propellants Explo Pyrotec

View full text Add to dashboard Cite

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“…Another drawback to weighing the fuel grain is that it does not provide data of local and instantaneous regression rates which is useful for validating regression rate models [54]. Other methods of regression rate measurement include using combustion chamber pressure [33], x-ray radiography [10], initial and final port diameter [26,46,54], and ultrasonic transducers [7,9,32]. More recently, [4] developed an imaging-based regression rate measurement for a 2D slab burner experiment.…”

Section: Introductionmentioning

confidence: 99%

Measurement of Hybrid Rocket Solid Fuel Regression Rate for a Slab Burner using Deep Learning

Surina,

Georgalis,

Aphale

et al. 2021

Preprint

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This study presents an imaging-based deep learning tool to measure the fuel regression rate in a 2D slab burner experiment for hybrid rocket fuels. The slab burner experiment is designed to verify mechanistic models of reacting boundary layer combustion in hybrid rockets by the measurement of fuel regression rates.A DSLR camera with a high intensity flash is used to capture images throughout the burn and the images are then used to find the fuel boundary to calculate the regression rate. A U-net convolutional neural network architecture is explored to segment the fuel from the experimental images. A Monte-Carlo Dropout process is used to quantify the regression rate uncertainty produced from the network. The U-net computed regression rates are compared with values from other techniques from literature and show error less than 10%. An oxidizer flux dependency study is performed and shows the U-net predictions of regression rates are accurate and independent of the oxidizer flux, when the images in the training set are not over-saturated. Training with monochrome images is explored and is not successful at predicting the fuel regression rate from images with high noise. The network is superior at filtering out noise introduced by soot, pitting, and wax deposition on the chamber glass as well as the flame when compared to traditional image processing techniques, such as threshold binary conversion and spatial filtering. U-net consistently provides low error image segmentations to allow accurate computation of the regression rate of the fuel.

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