The degree project arises from the interest in hybrid rocket engines since it is a modern global technology among rocket engines, and has not been built or tested in Colombia. The main objective of the project is to design, build and test a Design, build and test a 250 N hybrid thrust rocket motor. For this, the motor was designed with paraffin as the solid fuel, and nitrous oxide as the liquid oxidant when designing a methodology for design, construction and testing. In the conceptual design stage, different input parameters were defined, in which the pressure of the combustion chamber was 290 psi, nozzle temperature of 2856 K, flight time of 5 seconds, specific impulse of 185 seconds, with which the different elements of the combustion chamber could be designed, including the nozzle. Additionally, the oxidant tank and the valves system were designed for their subsequent manufacture and purchase, respectively. At the same time, the electronic system was proposed in order to measure the thrust, pressure in the combustion chamber and temperature in the nozzle; and the UCAND-3 benching test was redesigned to carry out the experiments, which were planned with a sample of three fuel grains. However, it was found that the igniter did not burn completely in any test to make the reaction between fuel and oxidant be carried out satisfactorily because the burning surface area was not enough for the reaction to take place, so it is necessary to change the ignition system. However, both the hybrid rocket engine and the benching test are ready to be used in the near future.

Hybrid Rocket Propulsion Design Handbook provides system scaling laws, design methodologies, and a summary of available test data, giving engineers all the tools they need to develop realistic hybrid system designs.Important supporting theory from chemistry, thermodynamics, and rocket propulsion is addressed, helping readers from a variety of backgrounds to understand this interdisciplinary subject. This book also suggests guidelines for standardized reporting of test data, in response to difficulties researchers have in working with results from different research institutes. - Covers general theory, recent advances and current fragmented experimental results of hybrid rocket engines - Outlines testing standards for hybrid researchers - Provides guidance on how to use a freely available online code from NASA

This is a textbook about rocket engineering, concentrating on the nitrous oxide hybrid rocket engine, both small and large. It's also a book about the science of chemical rockets in detail: three of the chapters are full of in-depth rocket science describing how all chemical rockets work. After a first chapter brushing up on the science and maths you'll need, the book describes the choice and safe use of hybrid rocket propellants, and how they're handled in practice. Then there are the rocket science chapters. Then you learn how to design, construct, and operate, a large hybrid rocket engine capable of getting you into Space. The book also includes a practical guide to the testing of hybrid rocket engines large and small, and how to fly them safely. 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.

The paper describes the design, construction, and testing of a liquid fueled rocket. Design calculations for the engine and propulsion systems were performed, checked, and an engine was constructed to those specifications. A static test stand was constructed and instrumented to evaluate engine performance during full duration static firings. The engine and propulsion system proved successful and were then incorporated into the flight vehicle. The remainder of the paper describes the design, construction, and testing of all flight hardware including an on-board camera system and recovery system. Two unsuccessful attempts to launch the missile were made on 11 May 1976 at White Sands Missile Range in New Mexico. The reasons for the failure were corrected and the missile was succesfully launched on 17 May 1976. (Author).

The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.

This book intends to build a bridge for the student and the young engineer: to link the rocket propulsion fundamentals and elements (which are well covered in the literature) with the actual rocket engine design and development work as it is carried out in industry (which is very little, if at all covered in literature). The book attempts to further the understanding of the realistic application of liquid rocket propulsion theories, and to help avoid or at least reduce time and money consuming errors and disappointments. In so doing, it also attempts to digest and consolidate numerous closely related subjects, hitherto often treated as separate, bringing them up to date at the same time.

This chapter briefly introduces hybrid rocket propulsion for general audience. Advantageous of hybrid rockets over solids and liquids are presented. This chapter also explains how to design a test setup for hybrid motor firings. Hybrid propulsion provides sustainable, safe and low cost systems for space missions. Therefore, this chapter proposes hybrid propulsion system for Mars Ascent Vehicles. Paraffin wax is the fuel of the rocket. Propulsion system uses CO2/N2O mixture as the oxidizer. The goal is to understand the ignition capability of the CO2 as an in-situ oxidizer on Mars. CO2 is known as major combustion product in the nature. However, it can only burn with metallic powders. Thus, metallic additives are added in the fuel grain. Results show that CO2 increase slows down the chemical kinetics thus reduces the adiabatic flame temperature. Maximum flammability limit is achieved at 75% CO2 by mass in the oxidizer mixture. Flame temperature is 1700 K at 75% CO2. Ignition quenches below the 1700 K.