Hybrid rocket nozzle design pdf

Figure 6motor design configuration nozzle the nozzle throat crosssectional area may be computed if the total propellant flow rate is. The design criteria, shown in italics in section 3, state clearly and briefly wha. Losses from conical shape not significant for our purposes. Design and analysis of aerospike nozzle to improve thrust in hybrid rocket engine t. The nozzle converts the chemical energy of the propellant into kinetic energy. The hybrid rocket concept can be traced back at least 75 years.

Design of nozzle for highpowered solid rocket propellant produced by the berkeley electronic press, 2018 figure 12. Basics of rocketry 6 propulsion basics what causes a rocket to move. I am working on developing an htpbn2o hybrid engine for my universitys competitive rocketry team. This design concept was developed using aerospike 2. The conditions for the rocket design were an o f ratio of 7. The first design was based on the model developed by the aeronautics and. Several design parameters of hybrid rocket motors were also evaluated and analyzed, including different fuel port geometry, type of fuels and oxidizers, number of ports, nozzle design and initial mass flux. Design of multiport grain with hydrogen peroxide hybrid rocket. How to design a solid rocket nozzle frog pond engineering. While the hybrid enjoys many safety and environmental advantages over conventional systems, large hybrids have not been commercially viable. The hybrid is inherently safer than other rocket designs. This is allowed if thermochemical environments are alike.

Mechanisms of graphite nozzle erosion in hybrid rockets huscap. Flightready hybrid rocket motor design during successful static fire test 82 33. This writeup on nozzle flow theory is based off of two main sources. Pdf flight research of an aerospike nozzle using high.

In the past, during a nozzle design procedure, the throat erosion was predicted by scaling experimental data to the analysed case. We show you how to design your own solid rocket nozzle using microsoft excel and fusion 360. Pdf design of a hybrid rocket motor progress in the. Rocket nozzle geometries georgia institute of technology. Hybrid propellant motor design kent evans, chris ryan, sam heyd, danny cha, johnny wang 22315 1. Included are full instructions for programming a rocket trajectory simulator in microsoft excel, and several appendices containing rocketry information and equations, and instructions on how to design a bell nozzle.

It was the first and only liquidfueled rocket engine to be reused from one mission to the next during the shuttle era. Hybrid propellant motor design 22315 washington state university. Design of the flightweight 900 lbf thrust hybrid rocket motor prior to construction of the flightweight 900 lbf thrust hybrid rocket motor, a series of hybrid rocket motors were designed, built and hotfire tested at the zucrow rocket test facilities. Hybrid rockets avoid some of the disadvantages of solid rockets like the dangers of propellant handling, while also avoiding some disadvantages of liquid rockets like their. Left aerospike integrated into smallscale hybrid rocket motor right 3d model. There are many kinds of nozzles, and many ways to manufacture them. Washington state university hybrid rocket team 18 our design 10,000ft. Nozzle fabrication was one of the pacing items in building an ssme. Words in bold appear in the glossary at the end of the document. The improvement of the space shuttle main engine ssme was a continuous undertaking, with the objectives being to increase.

A hybrid airbreathing rocket engine, sabre represents a huge advance over lace technology. Introduction to hybrid design the following is a short introduction to hybrid rocket engines, with some examples of the current state of hybrid research around the world. The fixed geometry hybrid engine postulated is composed of a primary rocket com ponent and a secondary scramjet component that includes an inlet, mixer, burner, and nozzle. This monograph, liquid rocket engine nozzles, was prepared under the direction of howard w. Preliminary study of a hybrid rocket mechanical engineering. Now, we will take a closer look at the state of the art with respect to hybrid rocket motor design focusing on oxidizer and fuel grain options oxidizers. Development and launch of the purdue hybrid rocket. Development of a reusable aerospike nozzle for hybrid. Design and analysis of reusable nozzles for cal polys hybrid. Ybrid rockets are rocket motor systems that use a solid fuel grain, and the other some type of liquid or gas as an oxidizer. Two aerospike rockets and one conventional rocket were flown successfully to supersonic speeds, providing the first known set of transonic flight performance data for aerospike rockets. Pdf hybrid rocket engine design with multiobjective vibrational. In the classical hybrid rocket motor, as the one in. The following section will detail simplified equations for the design of small liquidfuel rocket motors.

Hybrid rocket experiment station for capstone design, part 2 continued use edgar conley. The objectives incorporated into this phase of the design project include overall hybrid rocket layout, fuel grain design, oxidizer feed system, rocket nozzle design, ignition system, test. Design of a hybrid rocket motor injector head for internal. Cfd simulations of selfpressurized nitrous oxide hybrid. Rao back in 1958, when he derived analytically the wall contour of a nozzle by method of characteristics reference 1.

Characterization of hybrid rocket motor swirl injectors. Hybrid rocket motor is a tradeoff between the other two. Not only the engine preliminary design results, but also the simulation procedure. The nomenclature for the motor design is shown in figure 6. Ae6450 rocket propulsion design approaches from method of characteristics moc inviscid assumption can use hybrid approach for wall boundary layers must account for variable speed of sound. The test bed hybrid uses gaseous oxygen, gox, and a 2 dia plexiglas tube as the solid fuel. 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. A hybridpropellant rocket is a rocket with a rocket motor that uses rocket propellants in two different phases. This diagram is a basic model of how a liquid fuel rocket engine works.

Supersonic flow in cdnozzles presents a rich behaviour, with shock waves and expansion. The primary source is my notes from a fluid dynamics class on incompressible flows i recently took under professor gwynn elfring at the university of british columbia, while the secondary source is rocket propulsion elements by george p. Hybrid rocket motor aerospike nozzle tests youtube. The idea of the hybrid rocket is to store the oxidizer as a liquid and the fuel as a solid, producing a design that minimizes the chance of a chemical explosion.

All oxidizers for hybrids need to be in liquid form for it to be possible to reliably inject. 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. Douglass, chief, design criteria office, lewis research center. This paper describes the rockets, solid rocket motors, nozzles, and rocket instrumentation system. This motor is designed for airstart capability on the 2nd stage sustainer of a 2stage rocket with the 98mm amateur rocket standard motor diameter in mind. Method of characteristics pdf effects of particles in nozzle flow pdf. Design of nozzle for highpowered solid rocket propellant. Pdf design of a hybrid rocket motor progress in the perseus. Experimental high power rocketry is an extreme sport which offers makers a variety of opportunities to utilize their skills, obtain new skills, and explore. Deciding on the perhaps ubiquitus amongst amateurs, conical nozzle with 6015 deg. If a hybrid rocket motor nozzle is going to be designed the use of this scaling procedure can lead to an inaccurate design. The primary rocket burns hydrogen and oxygen in a stoichiometric mixture ratio. Design, analysis, and simulation of rocket propulsion system.

In this instructable i will introduce one method of making nozzles. Axial flow hybrid rocket derivation of the design equations for constant oxidizer flow rate, this expression can be integrated to obtain the port diameter as a function of time the instantaneous flux, regression rate, fuel mass flow rate, of can be calculated from based on of, total mass flow rate and nozzle geometry, one can. In line with rocketry convention, well sometimes use newtons fluxion notation. Following rocket propulsion elements guideline, the exit diameter of the divergent nozzle is five times the throat diameter, 0. A showerhead type design was adopted in the injector design. Actively cooled nozzles such as the the ssme and f1 nozzles were constructed by fabricating the individual tubes that made up the cooling channels 1080 tubes in the case of the ssme and brazing them together in an autoclave. This motor is designed for airstart capability on the 2nd stage sustainer of a 2stage rocket with the 98mm amateur rocket. Design and fabrication of a fullfeatured labscale hybrid rocket engine kyle platt university of central florida. Some of the key virtues of spgs hybrid rocket technology can be listed as see table for a summary. Effect of varying design options on the transient behavior.

Hybrid rocket experiment station for capstone design. Flight research has been conducted on an aerospike rocket nozzle using high power solid rockets. These design parameters bring a significant effect on hybrid rocket performance and size. Hybrid rocket design georgia institute of technology. Hybrid propellant motor design amazon web services. At nozzle throat area, m2 c do discharge coefficient for the injector design cf thrust coefficient c characteristic velocity, m. Design the nozzle will have a conical profile due to its proven performance and ease of manufacture. An overview we looked at the basic components of bipropellant, monopropellant, solid, and hybrid rocket motors. The science and design of the hybrid rocket engine. Flightready hybrid rocket motor design with tva assembly 82 32.

Design and analysis of aerospike nozzle to improve thrust. Activation and control of cpo shall be automatic with provision for manual control. A convergingdiverging nozzle condi nozzle, or cdnozzle, is the only one to get supersonic flows with m 1 when chocked. The history of rocket nozzles, specifically rao nozzle comes from g. Development of a portfolio of fast burning liquefying fuels mostly paraffinbased has enabled the use of a single circular port design approach which significantly simplifies the grain designprocessing and improves the fuel utilization to 98. Design and fabrication of a fullfeatured labscale hybrid. Simple nozzles are easy, but come with significant performance losses during off design operation many different nozzle types exist and are suitable for a variety of scenarios. The book also includes a practical guide to the testing of hybrid rocket engines large and small, and how to fly them safely. Washington state university hybrid rocket team 15 nozzles can be complex, and be adaptive for higher performance with changing altitude. Arrhenius, heat flux, erosion law, carbon erosion, performance losses, aerospike. Introduction pdf rocket nozzles and thrust pdf ideal nozzle fluid mechanics pdf nozzle design. Pdf in this study, the conceptual design of a singlestage hybrid rocket engine of a lowaltitude sounding rocket is developed using the. 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.