The following paragraphs explain the design concept for each section of the motor. Proposal for the inclusion of kno3sugar propellants to tra, october 4, 2002 page 4 1998 publication of rocket boys by homer hickam and subsequent movie october sky 1999 stirs new interest in rocketry, creating a distinct class of. Potassium nitrate acts as oxidizer and sugar serves as fuel, a 6535. The design criteria can serve effectively as a checklist of rules for the project manager to use in guiding a design or in assessing its adequacy. The nozzle is said to begin where the chamber diameter begins to decrease by the way, we assume the nozzle is axisymmetric, i. By solid fuel i mean that the propellant in the rocket engines is in a solid state such as a powder. It deals with everything from propellant formulations to nozzle design to thrust measurement to genuine rocket. The function of a rocket nozzle is to channelise and accelerate the combustion products produced by the burning propellant, inside a rocket motor, in such as way so as to maximize the velocity of the exhaust at the exit, to supersonic velocity. Im not really new but i did it all without calculate anything, just by trying progressively. Nirmith kumar mishra, dr s srinivas prasad, mr ayub padania. A sugar rocket is a simple home project that uses potassium nitrate kno3 and powdered sugar as fuel. The motor was loaded with three bates grains and testfired on a digital. Put on your safety glasses and leave them on for the rest of the project.
Completed sugar rocket, ready for launch daytime flight of a sugar rocket heres a crosssection of the 12inch id sugar fueled motors well be making. You will need an end cap for any sugar rocket motor that is case bonded, simply because the strength of adhesion of the sugar propellant to the case will not be strong enough for that last bit of propellant to actually burn, so all of that wasted mass might as well be burned more controlably. Greenwood, ed33, chief of the induced environment branch, aerophysics division, of the structures and dynamics laboratory. The usual configuration for a converging diverging cd nozzle is shown in the figure. The smallest crosssectional area of the nozzle is called the throat of the nozzle. Design and characterization of small solidpropellant rocket engine. Dualbell nozzle during testing at the nasa msfc ntf. This method could be used for the nozzle end but not for the upper closure because you couldnt put a motor with a grain already installed into the water. Methods are presented for measuring thrust using common force sensors and data acquisition to construct a dynamic force plate. To this end, the rockets are propelled by a solid mixture of sugar and potassium nitrate, a common fertilizer.
The design criteria, shown in italics in section 3, state clearly and briefly wha. This design concept was developed using aerospike 2. Automated nozzle design through axissymmetric method of. Design and analysis of aerospike nozzle to improve thrust in hybrid rocket engine t. Design and analysis of aerospike nozzle to improve thrust in. Nozzle is the exhaust duct of a rocket engines combustion chamber. Design and performance characteristics of a rocket using.
The first propellant, designated tf1 was drymixed knsucrose moistened with water and pressed into the motor tube. To date three major types of nozzles, the cone, the bell or contoured, and the annular or plug, have been employed. Ive been making rocket candy engines for over a year now as a cheaper alternative to commercially made motors. A jet nozzle will have a larger throat area and a lower chamber total pressure than a rocket nozzle. The motor casings are made from schedule 40 pvc water pipe. Using propep simulation software for the characterization of the sugar based propellant. Pdf design and analysis approach for linear aerospike nozzle. Each cad and any associated text, image or data is in no way sponsored by or affiliated with any company, organization or realworld item, product, or good it may purport to portray. See more ideas about rocket engine, diy rocket and rocket design. Sugar rocket motors can also be used in estestype model rockets, or to launch fireworks effects into the night sky. Propellant grain segment using white powder four types of rocket motor nozzles were used in this study. We built and tested rocket engines, varying the ratios of two main parts of the propellant the fuel and the oxidizer. Gases from propellant combustion are accelerated to higher velocities in the nozzle 10.
High powered rocket engines made from pvc pipe hackaday. Apr 05, 2018 the amount of thrust produced by the rocket depends on the mass flow rate through the engine, the exit velocity of the exhaust, and the pressure at the nozzle exit. The nozzle and header will use rockite anchor cement. Potassium nitrate based rocket propulsion tamir hasan, jay phillips. This makes enough propellant for a single 2long rocket motor. Im using a conical cake mold, and too often the nozzles come out with a very slight tilt which is immediately noticeable during launches. The warhead is filled with smuggled or scavenged tnt and urea nitrate, another common fertilizer.
Latest nozzle design for bigger motors be with a graphite insert. Design and analysis of aerospike nozzle to improve thrust. Potassium nitrate based rocket propulsion tamir hasan, jay phillips north carolina school of science and mathematics, durham, nc mentor. Main propulsion is provided by aerojets strutjet loxlh2 rocket based combined cycle engine design. Characterization of potassium nitrate sugar alcohol. Solid rocket motor for experimental sounding rockets. Measuring thrust and predicting trajectory in model rocketry. Completed sugar rocket, ready for launch daytime flight of a sugar rocket heres a crosssection of the 12inch id sugarfueled motors well be making. Paper open access experimental investigation of solid. Design analysis of mild steel combustion chamber for a sugar base. A rocket engine is a jet engine that uses specific propellant mass for forming high speedpropulsive exhaust jet.
The use of the axissymmetric method of characteristics coupled with niterate chemistry allows for the design and performance prediction of nozzles for liquid rocket engines. Now lets design a sugar motor for a hypothetical rocket. Find materials for this course in the pages linked along the left. Measuring thrust and predicting trajectory in model rocketry michael courtney and amy courtney ballistics testing group, p. The annular aerospike rocket motor pictured above left is a design developed and rendered by richard caldwell rocket nut intended to produce 225,000 pounds of thrust at sea level. The fuel in these rocket motors is powdered sugar or sucrose and the oxidizer is the potassium nitrate. How to make sugar rockets with potassium nitrate and. Sugar based rocket propulsion system making, analysis.
Old ones if they are too old will just snap, spraying boiling water out of the pan. I use a 60% potassium nitrate mix with 40% sugar, no additives. The oxidizer used was potassium nitrate, and the fuel was sorbitol. Homemade rocket can reach 2,300 feet for less than a dollar.
Possibly epoxy propellant or composite would work for both ends. When neglecting the effect of erosion during motor design, the chamber pressure can become. While its easy to make a sugar rocket, its also very dangerous, so use caution throughout your project. All of these variables depend on the design of the nozzle. We are going to design a motor using sugar and potassium nitrate. Tamir hasan potassium nitrate based rocket propulsion. Design and analysis approach for linear aerospike nozzle. Proposal for the inclusion of kno3sugar propellants to tra, october 4, 2002.
The design problem that has been considered is representative of an early preliminary engine design process. Hello, for anyone who uses rockite, durhams water putty, or some other variant for rocket nozzles, how do you make them properly symmetrical and straight. How to make quick and easy sugar rockets using potassium nitrate, sorbitol and red iron oxide. The amount of thrust produced by the rocket depends on the mass flow rate through the engine, the exit velocity of the exhaust, and the pressure at the nozzle exit.
For the casing we will use standard schedule 40 pvc pipe. Page 1 of 2 water putty rocket nozzles posted in rocketry. In most cases running a motor at lower pressure creates the biggest drop in performance of a propellant, it also slows the burn rate. The rockets presented in this book are of the simplest and use a solid fuel propellant. The computeraided design cad files and all associated content posted to this website are created, uploaded, managed and owned by third party users. The work to date falls into the following categories. Rocket nozzle shapes not all rocket nozzles are alike, and the shape selected usually depends on the application. Pdf solid rocket motors or srms are simple devices comprising of bulk head. These are the easiest ingredients to get normally and have been used for scores of years. This video describes how a typical convergingdiverging nozzle functio.
Pdf design analysis of mild steel combustion chamber for a. Design analysis of mild steel combustion chamber for a sugar base propellant of a solid rocket motor 30. How to make sugar rockets with potassium nitrate and sorbitol. Sep 10, 20 in this project, youll combine two commonly available substances granulated sugar and potassium nitrate to make a powerful engine that can propel a small sugar rocket to impressive heights.
Determination of a nozzle design, which accommodates. Rockets are powered by a propulsion device called rocket engine. These values are automatically passed to the aerospike nozzle analysis when the command button is clicked. The goal of amateur experimental rocketry aer, often simply referred to as amateur rocketry or experimental rocketry, is to design, build, test and launch rockets. Performance solid rocket motor srh submerged nozzlecombustion cavity flowfield assessment. Connection of flow to geometry we have considered the overall performance of a rocket and seen that is directly dependent on the exit velocity of the propellant. The utility of the qassam rocket design is assumed to be ease and speed of manufacture, using common tools and components. Automated nozzle design through axissymmetric method of characteristics coupled with chemical kinetics by reid britton young a thesis submitted to the graduate faculty of auburn university in partial ful llment of the requirements for the degree of master of science auburn, alabama august 4, 2012 keywords.
Therefore, the purpose of this project was to design a reusable highpowered rocket capable of deploying a five pound cosmic ray detector at 10,000 feet by designing the structure, propulsion system, and avionics section. Gas flows through the nozzle from a region of high pressure usually referred to as the chamber to one of low pressure referred to as the ambient or tank. The nozzle converts the chemical energy of the propellant into kinetic energy with no moving parts. The pvc rocket motors may be broken down into 4 main sections. Multidisciplinary approach to aerospike nozzle design. It might look interesting because it kind of looks like the shape of a nozzle, even though the real nozzle is. Further, we have used the steady flow energy equation to determine the exhaust velocity using the combustion chamber conditions and the nozzle exit pressure. The report presents a design and structure of a strand burner, raw data and a method of calculations for burning rate. In a rocket engine the propellant burns and produces these gases, which inside a closed space. While the physics is the same for both types of nozzles, the limits on the flow variables are typically different. E28, e33, e39, e49, e54, f62, and f67 motor designs. Everything i do is based on sugar propellants but most also will work for any other type of propellant. The conceptual design for phase iii of the flightresearch campaign will be detailed in a future publication.
The fuel in these rocket motors is powdered sugar or sucrose and the oxidizer is the. Oct 04, 2019 you can design a turbojet nozzle or a rocket nozzle by using the choice button at the top. Candy propellant moulded mixture of potassium nitrate and sugar fuel. How to design a sugar rocket nozzle in rocket propulsion analysis rpa i show you how to use rpa to design your very own solid rocket nozzle. Just a few pages here to show some of my motor development projects. Abhijeet singh department of aerospace engineering mlr institute of technology, dundigal village quthbullapur mandal, hyderabad telangana india abstract a solid rocket or a solidfuel rocket is a rocket with a motor that uses solid propellants fueloxidizer. This section discusses the basic characteristics of the major classes of nozzles used today. I cant find any information about how to design one of those, anyone knows a book or something. I have already had success with pvc and paper case rockets with a ratio of 18 mm id to 5 mm nozzle all the way up the pipe. The nasamsfc contracting officers representative for this contract was dr. Although the thrust vector control mechanism is also a component of many rocket motors, it is described separately in chapter 16. For more information on characterizing rocket motors and capturing and processing data from test burns please see my instructable on that topic.
Using the scale, measure 14 grams of potassium nitrate or saltpeter kno3 and 7 grams of sugar. Where to download space propulsion analysis and design ronald humblespace propulsion analysis and design. Rocket motor design the rocket motor consists of head cap, combustion chamber, nozzle, igniter charge, and propellant grain segment, as can be seen in figure 4. In this context, rocket may refer to the motor itself, or to a complete vehicle that consists of motor, fuselage and stabilizing devices such as fins, nosecone, and payload. The propellant is a mixture of a fuel and an oxidizer. That data is used by burnsim to design a flight motor. Rocket motors and propellants are selfdesigned and selfmade.
It is very easy to work with, sets quick but not too. The use of a particle swarm pattern search optimizer enables viable pressure distributions to initiate the axissymmetric method of characteristics. In addition to propellant characteristics, a motor must be planned and designed. Burnsim is the authors tool of choice for designing a rocket motor. The nozzle converts the chemical energy of the propellant into kinetic energy. The specific heat of chamber cpcv of the formula is also needed to design a nozzle. Afterwards a layer of epoxy covered the nozzle end surface of the grain. Highperformance rocket nozzle concept article pdf available in journal of propulsion and power 265. Potassium nitrate based rocket propulsion aerocon systems.