Name: Improving the Combustion Performance of a Hybrid Rocket Engine using a Novel Fuel Grain with a Nested Helical Structure (Video) | JoVE Journal
Uploaded: 2021-01-18T12:30:00.000+00:00
Duration: 7 min 58 s
Description: Learn to improve combustion performance in hybrid rocket engines using a novel nested helical fuel grain structure. This method maintains fuel integrity during combustion and enhances efficiency.

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5 minutes

This work was supported by the National Natural Science Foundation of China (Grant Nos. 11802315, 11872368 and 11927803) and Equipment Pre-Research Foundation of National Defense Key Laboratory (Grant No. 6142701190402).

1. Experimental setup and procedures
<ol>
	<li>Preparation of fuel grain 
	NOTE: The fuel grain with novel structure consisted of two parts, which are shown in Figure 4. As the main part of the novel grain, the paraffin-based fuel accounts for more than 80% of the total mass. The ABS substrate is used as an additional fuel. The preparation of this fuel grain was realized by combining 3D printing and centrifugal casting.
	<ol>
		<li>Substrate preparation
		<ol>
			<li>Open 3D software for ABS substrate drawing. 
			NOTE: The ABS substrate, which intended to provide the helical framework and support for the paraffin-based fuel, is comprised of twelve integrated blades that rotate 360° clockwise in the axial direction and the wall.</li>
			<li>Save the 3D structure of the ABS substrate as a STL file.</li>
			<li>Open the 3D slicing software and import the structure of ABS substrate.</li>
			<li>Click Start Slicing, and select Speed print mode from Main Template. 
			NOTE: For the Primary Extruder choose ABS 1.75 mm.</li>
			<li>Double-click Speed, change the infill density to 100% and select Raft with Skirt for the Platform Addition. 
			NOTE: In order to improve the print quality and prevent warping, it is necessary to use a structure of print base (Raft with Skirt) to increase the contact area between the print body and the bottom plate.</li>
			<li>Click Save and Close, and then click Slice.</li>
			<li>Turn on the 3D printer and import the ABS substrate slice file.</li>
			<li>Set the temperature of the heated bed and nozzle to 100 and 240 °C, respectively.</li>
			<li>Click Start to print after stabilization.</li>
		</ol>
		</li>
		<li>Paraffin-based fuel preparation
		<ol>
			<li>Prepare raw materials of paraffin, polyethylene (PE) wax, stearic acid, ethylene-vinyl acetate (EVA), and carbon powder. Configure the paraffin-based fuel according to the ratio of these components as 0.58:0.2:0.1:0.1:0.02. 
			NOTE: The specific information of each raw material is shown in the material table. The distribution ratio of paraffin-based fuel is not fixed and can be adjusted appropriately according to the purpose of the experiment. The purpose of adding carbon powder is to block radiant heat transfer and prevent the fuel grain from softening and collapsing during combustion.</li>
			<li>Place the configured raw materials into the melt mixer, and fully melt and stir until completely mixed. 
			NOTE: The paraffin-based fuel is heated to 120 °C to ensure complete melting while preventing deformation of the ABS blades.</li>
		</ol>
		</li>
		<li>Fuel grain manufacturing 
		NOTE: To better demonstrate the effect of improving the combustion performance, paraffin-based fuel grains with the same composition were set as the control.
		<ol>
			<li>Place the ABS substrate into the centrifuge, and secure it with an end cap.</li>
			<li>Plug in the power and turn on the water-cooling pump switch.</li>
			<li>Turn on the centrifuge relay and increase the speed to 1400 rpm.</li>
			<li>Open the valve on the melt mixer and start casting. 
			NOTE: The molten paraffin-based fuel flows into the initial section of mold through the pipe and the end cover with a central opening. Under the effect of gravity, the liquid fuel spreads along the axial direction of the mold. Combined with effective cooling, a multiple-casting method, which is to divide the original one-time filling process into multiple times, is required to reduce the thermal stress.</li>
			<li>Remove the fuel grain and trim the shape.</li>
		</ol>
		</li>
		<li>Fuel grain measurement and recording
		<ol>
			<li>Measure and record the weight, length, and inner diameter of the fuel grain.</li>
			<li>Photograph the complete fuel grain.</li>
		</ol>
		</li>
	</ol>
	</li>
	<li>Preparation of hybrid rocket engine system 
	NOTE: As shown in Figure 5, the hybrid rocket engine system consisted of four parts: the supply system, the ignition system, the engine, and the measurement and control system. The engine part included five parts: the torch igniter, the head, the combustion chamber, the post-combustion chamber, and the nozzle. The total length of the hybrid rocket engine is about 300 mm, and the inner diameter of the combustion chamber is 70 mm.
	<ol>
		<li>Hybrid rocket engine assembly 
		NOTE: The exhaustive details of the laboratory-scale hybrid rocket and the composition of the experimental system can be found in the previous paper32.
		<ol>
			<li>Fix the combustion chamber section of hybrid rocket engine on the slide rail.</li>
			<li>Load the fuel grain and install the post-combustion chamber section.</li>
			<li>Install the head and nozzle.</li>
			<li>Install the torch igniter on the head of the hybrid rocket engine.</li>
			<li>Install the spark plug and connect the power supply.</li>
		</ol>
		</li>
		<li>Connect the nitrogen, oxidizer, ignition methane, and ignition oxygen gas supply lines between the test bench and the gas cylinder.</li>
		<li>Connect the industrial computer, the multi-function data acquisition card, the mass flow controller, and the control box of the test bench.</li>
		<li>Power on the test bench, the mass flow controller, and the igniter.</li>
	</ol>
	</li>
	<li>Check the test system and set the experimental conditions.
	<ol>
		<li>Open the FlowDDE software and click Communications settings from the Communication.</li>
		<li>Click the corresponding connection interface and click OK.</li>
		<li>Click Open communication to establish communication with the flow controller and open the measurement and control program (MCP).</li>
		<li>Set the I/O channel of the multi-function data acquisition card and click Run to establish communication with the entire system.</li>
		<li>Check MCP running status and set to manual control mode. 
		NOTE: The MCP includes two modes: manual control is used for debugging and automatic control is used during experiments. The MCP written by LabVIEW is shown in Figure 6.</li>
		<li>Check the working condition of the spark plug and perform a valve test.</li>
		<li>Test data recording function.</li>
		<li>Open the setting interface and set test time, including valve opening and closing time, ignition time, and data recording duration. 
		NOTE: It takes some time for the mass flow controller to regulate the oxidizer flow to the set value, so the ignition time was set to 2 s after the supply of oxidizer.</li>
		<li>Set safety requirements and clear personnel from the experimental area.</li>
		<li>Open the cylinder valve and adjust the output pressure of the regulating valve according to the different mass flow rate conditions. 
		NOTE: With the supply pressure of 6MPa, the range of mass flow rate of the oxidizer is between 7 g/s and 29 g/s.</li>
		<li>Open the setting interface and set the oxidizer mass flow rate.</li>
	</ol>
	</li>
	<li>Hybrid rocket engine ignition
	<ol>
		<li>Turn on the camera.</li>
		<li>Set the MCP to automatic control mode and wait for trigger.</li>
		<li>Click Start on the MCP to start the experiment.</li>
		<li>After about one minute, click Stop on the MCP and turn off the camera.</li>
		<li>Close the gas cylinder and open the valve in the pipeline to relieve the pressure.</li>
		<li>Power off the test bench and remove the fuel grain.</li>
		<li>Repeat Step 1.1.4.</li>
	</ol>
	</li>
</ol>
2. Analysis of combustion performance
<ol>
	<li>Analysis of pressure oscillation 
	NOTE: The saved combustion chamber pressure data is represented as Pc(t).
	<ol>
		<li>Open Pc(t) with the data processing software.</li>
		<li>Choose the time period during the combustion process of the hybrid rocket engine.</li>
		<li>Select Analysis &gt; Signal Processing &gt; FFT to analyze the pressure oscillation.</li>
		<li>Use the default settings and click OK.</li>
	</ol>
	</li>
	<li>Analysis of regression rate
	<ol>
		<li>Calculate the regression rate of the fuel grain according to the following function: 
		<img alt="Equation for diffusion rate; mathematical formula; scientific research; process analysis." src="/files/ftp_upload/61555/61555equ01v2.jpg" data-altupdatedat="1788250015000" data-alt="Equation 1"> 
		where ΔD represent the change of average inner diameters of the solid fuel grain after the firing test; <img alt="Static equilibrium equation Δmₓ, formula for force balance analysis, used in physics diagrams." src="/files/ftp_upload/61555/61555equ05.jpg" data-altupdatedat="1788250015000" data-alt="Equation 5"> represent the change of quality of the fuel grain; L is the length of the fuel grain; ρ is the average density of the solid fuel; t is the working time. 
		NOTE: The average density ρ of the novel grain was expressed as: 
		<img alt="Static equilibrium equation, ρ=ρpωp+ρABSωABS, shown in formula chart for physics study." src="/files/ftp_upload/61555/61555equ02v2.jpg" data-altupdatedat="1788250015000" data-alt="Equation 2"> 
		where <img alt="Static equilibrium, formula ΣFx=0, diagram, educational physics study, forces balance, analysis." src="/files/ftp_upload/61555/61555equ06.jpg" data-altupdatedat="1788250015000" data-alt="Equation 6"> and <img alt="Static equilibrium, ΣFx=0, mechanical balance diagram, educational physics, force analysis setup." src="/files/ftp_upload/61555/61555equ07.jpg" data-altupdatedat="1788250015000" data-alt="Equation 7"> represent the density of the nested paraffin-based fuel and ABS material, respectively; <img alt="Plasma frequency equation ωₚ diagram illustrating electron oscillation and electromagnetic wave behavior." src="/files/ftp_upload/61555/61555equ08.jpg" data-altupdatedat="1788250015000" data-alt="Equation 8"> and <img alt="Static equilibrium, ΣFx=0, diagram; showcases forces balance in mechanical setup." src="/files/ftp_upload/61555/61555equ09.jpg" data-altupdatedat="1788250015000" data-alt="Equation 9"> represent the mass fraction of the nested paraffin-based fuel and ABS material, respectively.</li>
		<li>Fit the regression rate as a function of oxidizer flux. 
		NOTE: The fitting function was selected as Allometric1 <img alt="power-law equation \(y=ax^b\) in relation to data analysis chart" src="/files/ftp_upload/61555/61555equ10.jpg" data-altupdatedat="1788250015000" data-alt="Equation 10">, and the iterative algorithm was selected as Levenberg–Marquardt optimization algorithm.</li>
	</ol>
	</li>
	<li>Analysis of combustion efficiency
	<ol>
		<li>Calculate average combustion chamber pressure Pc by the following function: 
		<img alt="Calculating average probability equation; Σ(Pc(t))/n, mathematical formula, educational use." src="/files/ftp_upload/61555/61555equ03v2.jpg" data-altupdatedat="1788250015000" data-alt="Equation 3"> 
		where Pc(t) represents the combustion chamber pressure at different times; t1 and tn represent the initial and final times at which the combustion chamber pressure was greater than 50% of the average pressure, respectively; n represents the number of pressure data points between and t1 and tn.</li>
		<li>Calculate the combustion characteristic velocity C⃰ according to the following function: 
		<img alt="Equation for thrust coefficient, \(C^* = \frac{P_c A_t}{\dot{m}}\), in propulsion analysis." src="/files/ftp_upload/61555/61555equ04v2.jpg" data-altupdatedat="1788250015000" data-alt="Equation 4"> 
		where Pc is the average combustion chamber pressure; At is the throat area; ḿ is the total mass flow rate.</li>
		<li>Calculate the theoretical characteristic velocity of paraffin fuel C⃰P by NASA CEA code33.</li>
	</ol>
	</li>
</ol>

<ol><li>Boiron, A. J., Cantwell, B. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aBoiron%2C+AJ+%2249th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference%22">49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference</a>. , (2013).</li>
<li>Mazzetti, A., Merotto, L., Pinarello, G. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Paraffin-based+hybrid+rocket+engines+applications%3A+A+review+and+a+market+perspective%5BTitle%5D)+AND+%22Acta+Astronautica%22%5BJournal%5D)">Paraffin-based hybrid rocket engines applications: A review and a market perspective.</a> Acta Astronautica. 126, 286-297 (2016).</li>
<li>Karabeyoglu, A., Zilliac, G., Cantwell, B. J., DeZilwa, S., Castellucci, P. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Scale-Up+Tests+of+High+Regression+Rate+Paraffin-Based+Hybrid+Rocket+Fuels%5BTitle%5D)+AND+%22Journal+of+Propulsion+and+Power%22%5BJournal%5D)">Scale-Up Tests of High Regression Rate Paraffin-Based Hybrid Rocket Fuels.</a> Journal of Propulsion and Power. 20 (6), 1037-1045 (2004).</li>
<li>Jens, E. T., Narsai, P., Cantwell, B., Hubbard, G. S. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aJens%2C+ET+%2250th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference%22">50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference</a>. , (2014).</li>
<li>Kuo, K. K., Chiaverini, M. J. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aKuo%2C+KK+%22Fundamentals+of+Hybrid+Rocket+Combustion+and+Propulsion%22">Fundamentals of Hybrid Rocket Combustion and Propulsion</a>. , (2007).</li>
<li>Boardman, T., et al. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aBoardman%2C+T+%2233rd+Joint+Propulsion+Conference+and+Exhibit%22">33rd Joint Propulsion Conference and Exhibit</a>. , (1997).</li>
<li>Connell, T. L., et al. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Enhancement+of+Solid+Fuel+Combustion+in+a+Hybrid+Rocket+Motor+Using+Amorphous+Ti-Al-B+Nanopowder+Additives%5BTitle%5D)+AND+%22Journal+of+Propulsion+and+Power%22%5BJournal%5D)">Enhancement of Solid Fuel Combustion in a Hybrid Rocket Motor Using Amorphous Ti-Al-B Nanopowder Additives.</a> Journal of Propulsion and Power. 35 (3), 662-665 (2019).</li>
<li>Veale, K., Adali, S., Pitot, J., Brooks, M. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((A+review+of+the+performance+and+structural+considerations+of+paraffin+wax+hybrid+rocket+fuels+with+additives%5BTitle%5D)+AND+%22Acta+Astronautica%22%5BJournal%5D)">A review of the performance and structural considerations of paraffin wax hybrid rocket fuels with additives.</a> Acta Astronautica. 141, 196-208 (2017).</li>
<li>Karakas, H., Kara, O., Ozkol, I., Karabeyoglu, A. M. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aKarakas%2C+H+%22AIAA+Propulsion+and+Energy+2019+Forum%22">AIAA Propulsion and Energy 2019 Forum</a>. , (2019).</li>
<li>Di Martino, G. D., Mungiguerra, S., Carmicino, C., Savino, R. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Computational+fluid-dynamic+modeling+of+the+internal+ballistics+of+paraffin-fueled+hybrid+rocket%5BTitle%5D)+AND+%22Aerospace+Science+and+Technology%22%5BJournal%5D)">Computational fluid-dynamic modeling of the internal ballistics of paraffin-fueled hybrid rocket.</a> Aerospace Science and Technology. 89, 431-444 (2019).</li>
<li>Leccese, G., Cavallini, E., Pizzarelli, M. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aLeccese%2C+G+%22AIAA+Propulsion+and+Energy+2019+Forum%22">AIAA Propulsion and Energy 2019 Forum</a>. , (2019).</li>
<li>Cardoso, K. P., Ferrão, L. F. A., Kawachi, E. Y., Gomes, J. S., Nagamachi, M. Y. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Ballistic+Performance+of+Paraffin-Based+Solid+Fuels+Enhanced+by+Catalytic+Polymer+Degradation%5BTitle%5D)+AND+%22Journal+of+Propulsion+and+Power%22%5BJournal%5D)">Ballistic Performance of Paraffin-Based Solid Fuels Enhanced by Catalytic Polymer Degradation.</a> Journal of Propulsion and Power. 35 (1), 115-124 (2019).</li>
<li>Paccagnella, E., Barato, F., Pavarin, D., Karabeyoğlu, A. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Scaling+Parameters+of+Swirling+Oxidizer+Injection+in+Hybrid+Rocket+Motors%5BTitle%5D)+AND+%22Journal+of+Propulsion+and+Power%22%5BJournal%5D)">Scaling Parameters of Swirling Oxidizer Injection in Hybrid Rocket Motors.</a> Journal of Propulsion and Power. 33 (6), 1378-1394 (2017).</li>
<li>Kumar, R., Ramakrishna, P. A. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Effect+of+protrusion+on+the+enhancement+of+regression+rate%5BTitle%5D)+AND+%22Aerospace+Science+and+Technology%22%5BJournal%5D)">Effect of protrusion on the enhancement of regression rate.</a> Aerospace Science and Technology. 39, 169-178 (2014).</li>
<li>Kumar, R., Ramakrishna, P. A. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Enhancement+of+Hybrid+Fuel+Regression+Rate+Using+a+Bluff+Body%5BTitle%5D)+AND+%22Journal+of+Propulsion+and+Power%22%5BJournal%5D)">Enhancement of Hybrid Fuel Regression Rate Using a Bluff Body.</a> Journal of Propulsion and Power. 30 (4), 909-916 (2014).</li>
<li>Degges, M. J., et al. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aDegges%2C+MJ+%2249th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference%22">49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference</a>. , (2013).</li>
<li>Connell, T., Young, G., Beckett, K., Gonzalez, D. R. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aConnell%2C+T+%22AIAA+Scitech+2019+Forum%22">AIAA Scitech 2019 Forum</a>. , (2019).</li>
<li>Whitmore, S., Peterson, Z., Eilers, S. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aWhitmore%2C+S+%2247th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference+%26+Exhibit%22">47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit</a>. , (2011).</li>
<li>Whitmore, S. A., Armstrong, I. W., Heiner, M. C., Martinez, C. J. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aWhitmore%2C+SA+%222018+Joint+Propulsion+Conference%22">2018 Joint Propulsion Conference</a>. , (2018).</li>
<li>Whitmore, S. A., Peterson, Z. W., Eilers, S. D. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Comparing+Hydroxyl+Terminated+Polybutadiene+and+Acrylonitrile+Butadiene+Styrene+as+Hybrid+Rocket+Fuels%5BTitle%5D)+AND+%22Journal+of+Propulsion+and+Power%22%5BJournal%5D)">Comparing Hydroxyl Terminated Polybutadiene and Acrylonitrile Butadiene Styrene as Hybrid Rocket Fuels.</a> Journal of Propulsion and Power. 29 (3), 582-592 (2013).</li>
<li>Whitmore, S. A., Sobbi, M., Walker, S. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aWhitmore%2C+SA+%2250th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference%22">50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference</a>. , (2014).</li>
<li>Whitmore, S. A., Walker, S. D. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Engineering+Model+for+Hybrid+Fuel+Regression+Rate+Amplification+Using+Helical+Ports%5BTitle%5D)+AND+%22Journal+of+Propulsion+and+Power%22%5BJournal%5D)">Engineering Model for Hybrid Fuel Regression Rate Amplification Using Helical Ports.</a> Journal of Propulsion and Power. 33 (2), 398-407 (2017).</li>
<li>Creech, M., et al. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aCreech%2C+M+%2253rd+AIAA+Aerospace+Sciences+Meeting%22">53rd AIAA Aerospace Sciences Meeting</a>. , (2015).</li>
<li>Lyne, J. E., et al. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aLyne%2C+JE+%222018+Joint+Propulsion+Conference%22">2018 Joint Propulsion Conference</a>. , (2018).</li>
<li>Elliott, T. S., et al. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aElliott%2C+TS+%2252nd+AIAA%2FSAE%2FASEE+Joint+Propulsion+Conference%22">52nd AIAA/SAE/ASEE Joint Propulsion Conference</a>. , (2016).</li>
<li>Armold, D., et al. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aArmold%2C+D+%2249th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference%22">49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference</a>. , (2013).</li>
<li>Armold, D. M., et al. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aArmold%2C+DM+%2250th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference%22">50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference</a>. , (2014).</li>
<li>Fuller, J., Ehrlich, D., Lu, P., Jansen, R., Hoffman, J. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aFuller%2C+J+%2247th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference+%26+Exhibit%22">47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit</a>. , (2011).</li>
<li>Lee, C., Na, Y., Lee, J. W., Byun, Y. H. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Effect+of+induced+swirl+flow+on+regression+rate+of+hybrid+rocket+fuel+by+helical+grain+configuration%5BTitle%5D)+AND+%22Aerospace+Science+and+Technology%22%5BJournal%5D)">Effect of induced swirl flow on regression rate of hybrid rocket fuel by helical grain configuration.</a> Aerospace Science and Technology. 11 (1), 68-76 (2007).</li>
<li>Tian, H., Li, Y., Li, C., Sun, X. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Regression+rate+characteristics+of+hybrid+rocket+motor+with+helical+grain%5BTitle%5D)+AND+%22Aerospace+Science+and+Technology%22%5BJournal%5D)">Regression rate characteristics of hybrid rocket motor with helical grain.</a> Aerospace Science and Technology. 68, 90-103 (2017).</li>
<li>Hitt, M. A. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aHitt%2C+MA+%222018+Joint+Propulsion+Conference%22">2018 Joint Propulsion Conference</a>. , (2018).</li>
<li>Wang, Z., Lin, X., Li, F., Yu, X. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Combustion+performance+of+a+novel+hybrid+rocket+fuel+grain+with+a+nested+helical+structure%5BTitle%5D)+AND+%22Aerospace+Science+and+Technology%22%5BJournal%5D)">Combustion performance of a novel hybrid rocket fuel grain with a nested helical structure.</a> Aerospace Science and Technology. 97, (2020).</li>
<li>McBride, J. B., Gordon, S. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aMcBride%2C+JB+%22Computer+Program+for+Calculation+of+Complex+Chemical+Equilibrium+Compositions+and+APPlications%22">Computer Program for Calculation of Complex Chemical Equilibrium Compositions and APPlications</a>. , (1996).</li>
<li>De Zilwa, S., Zilliac, G., Karabeyoglu, A., Reinath, M. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aDe+Zilwa%2C+S+%2239th+AIAA%2FASME%2FSAE%2FASEE+Joint+Propulsion+Conference+and+Exhibit%22">39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit</a>. , (2003).</li>
<li>Franco, M., et al. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Regression+Rate+Design+Tailoring+Through+Vortex+Injection+in+Hybrid+Rocket+Motors%5BTitle%5D)+AND+%22Journal+of+Spacecraft+and+Rockets%22%5BJournal%5D)">Regression Rate Design Tailoring Through Vortex Injection in Hybrid Rocket Motors.</a> Journal of Spacecraft and Rockets. 57 (2), 278-290 (2020).</li>
</ol>

The authors have nothing to disclose.

The technique presented in this paper is a novel approach using a fuel grain with a nested helical structure. There are no difficulties in setting up the necessary equipment and facilities. The helical structure can be easily produced by 3D printing, and nesting of paraffin-based fuels can be easily carried out by centrifugal casting. Fused deposition molding (FDM) 3D printers are not expensive and the cost of centrifuges is low.
When the inner surface of the shaped fuel grain was found to hav...

A technique to improve the combustion performance of a hybrid rocket engine is urgently required. To date, practical applications of hybrid rocket engines are still far less than those of solid and liquid rocket engines1,2. The low regression rate of traditional fuels limits the improvement of thrust performance for the hybrid rocket engine3,4. In addition, its combustion efficiency is slightly lower than that of other chemical energy rockets due to internal diffusion combustion5, as shown in Figure 1. Although various techniques have been studied and developed, such as the use of multi-ports6, enhancing additives7,8,9, liquefying fuel10,11,12, swirl injection13, protrusions14, and bluff body15, these approaches are associated with problems in volume utilization, combustion efficiency, mechanical performance, and redundancy quality. Thus far, structural improvement of the fuel grain, which does not have these shortcomings, has attracted more attention as an effective means of improving combustion performance16,17. The advent of three-dimensional (3D) printing has brough an effective way to increase the performance of hybrid rocket engines through the ability to rapid and inexpensively produce either complex conventional grain designs or nonconventional fuel grains18,19,20,21,22,23,24,25,26,27,28,29,30. However, during the combustion process, these improvements in combustion performance diminishes with the characteristic structure burning, resulting in a decrease in combustion performance23. We have demonstrated that a novel design is useful in improving performance of hybrid rocket engines31. The detail for this technique and representative results is presented in this paper.
The fuel grain consists of a helical substrate made by acrylonitrile-butadiene-styrene (ABS) and a nested paraffin-based fuel. Based on centrifugal and 3D printing, the advantages of the two fuels with different regression rates were combined. The special helical structure of the fuel grain after combustion is shown in Figure 2. When gas passes through the fuel grain, numerous recirculation zones are simultaneously created at grooves between blades, which is shown in Figure 3. This characteristic structure on the inner surface increases the turbulence kinetic energy and swirl number in the combustion chamber, which increase the exchanges of both matter and energy in the combustion chamber. Ultimately, the regression rate of the novel fuel grain is effectively improved. The effect of improving the regression rate has been well proven: in particular, the regression rate of the novel fuel grain was demonstrated to be 20% higher than that of the paraffin-based fuel at the mass flux of 4 g/s&#183;cm2,32.
One advantage of the fuel grain with a nested helical structure is that it is simple to manufacture. The molding process mainly requires a melt mixer, a centrifuge, and a 3D printer. The ABS substrate formed by 3D printing greatly reduces the manufacturing cost. Another significant and unique advantage is that the enhancement effect does not disappear during the combustion process.
This paper presents the experimental system and procedure for improving the combustion performance of a hybrid rocket engine using the novel fuel grain structure. Additionally, this paper presents three representative comparisons of combustion performance parameters to prove the feasibility of the technique, including oscillation frequency of combustion chamber pressure, regression rate, and combustion efficiency characterized by characteristic velocity.

<table><tbody><tr><td>3D printer</td><td>Raise3D</td><td>N2 Plus</td><td>305 &amp;times; 305 &amp;times; 605 mm</td></tr><tr><td>3D drawing software</td><td>Autodesk</td><td>Inventor</td><td></td></tr><tr><td>ABS</td><td>Raise3D</td><td>ABS black</td><td>1.75 mm</td></tr><tr><td>Camera</td><td>Sony</td><td>A6000</td><td></td></tr><tr><td>Carbon</td><td>Aibeisi</td><td>ATP-88AT</td><td></td></tr><tr><td>Centrifugal machine</td><td>Luqiao Langbo Motor Co.Ltd</td><td>Custom</td><td>&amp;le;1450 rpm</td></tr><tr><td>Data processing software</td><td>OriginLab</td><td>Origin 2020</td><td></td></tr><tr><td>EVA</td><td>DuPont Company</td><td>360</td><td>binder</td></tr><tr><td>Mass flow controller</td><td>Bronkhost</td><td>F-203AV</td><td>0-1500 ln/min</td></tr><tr><td>Melt mixer</td><td>Winzhou Chengyi Jixie Co.Ltd</td><td>Custom</td><td></td></tr><tr><td>Multi-function data acquisition card</td><td>NI</td><td>USB-6211</td><td></td></tr><tr><td>Paraffin</td><td>Sinopec Group Company</td><td>58#</td><td>Fully refined paraffin, Melting point&amp;#8776;58&amp;deg;C</td></tr><tr><td>PE wax</td><td>Qatar petroleum chemical industry Company</td><td>Custom</td><td></td></tr><tr><td>Slicing software</td><td>Raise3D</td><td>ideaMaker</td><td></td></tr><tr><td>Spark plug</td><td>NGK</td><td>PFR7S8EG</td><td></td></tr><tr><td>Stearic acid</td><td>ical Reagent Company</td><td>Custom</td><td>hardener</td></tr></tbody></table>

improving the combustion performance of a hybrid rocket engine using a novel fuel grain with a nested helical structure

Improving the Combustion Performance of a Hybrid Rocket Engine using a Novel Fuel Grain with a Nested Helical Structure

A technique to improve the combustion performance of a hybrid rocket engine using a novel fuel grain structure is presented. This technique utilizes the different regression rates of acrylonitrile butadiene styrene and paraffin-based fuels, which increase the exchanges of both matter and energy by swirl flow and recirculation zones formed at the grooves between the adjacent vanes. The centrifugal casting technique is used to cast the paraffin-based fuel into an acrylonitrile butadiene styrene substrate made by three-dimensional printing. Using oxygen as the oxidizer, a series of tests were conducted to investigate the combustion performance of the novel fuel grain. In comparison to paraffin-based fuel grains, the fuel grain with a nested helical structure, which can be maintained throughout the combustion process, showed significant improvement in the regression rate and great potential in improvement of combustion efficiency.

Figure 7 shows the changes in combustion chamber pressure and oxidizer mass flow rate. To provide the necessary time for flow regulation, the oxidizer enters the combustion chamber in advance. When the engine builds pressure in the combustion chamber, the oxygen mass flow rate drops rapidly and then maintains a relatively steady change. During the combustion process, the pressure in the combustion chamber remains relatively stable.
Images showing a comparison of c...

A technique utilizing a solid fuel grain with a novel nested helical structure to improve the combustion performance of a hybrid rocket engine is presented.

A technique to improve the combustion performance of a hybrid rocket engine using a novel fuel grain structure is presented. This technique utilizes the ...

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Research

JoVE Journal

Engineering

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Learn to improve combustion performance in hybrid rocket engines using a novel nested helical fuel grain structure. This method maintains fuel integrity during combustion and enhances efficiency.

Improving the Combustion Performance of a Hybrid Rocket Engine using a Novel Fuel Grain with a Nested Helical Structure

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