Goddard Launches the First Liquid Fuel Propelled Rocket

1977

In the early 20th century, many early rocket pioneers favored liquid hydneen; however, mne of them used hydrogen as a rocket fie1 because of its extreme physical properties and scarcity. difficult is a boiling point of-426O at one atmosphere, and a density about one-seventh that of water. Interest in the methods and apparatus used i n hydrogen gas liquefaction increased sigrdficantly in the mid-1940s when handling methods w e r e developed t o supply liquid hydrogen f o r the steadily increasing requirements of basic research. The authors had the good fortune t o participate i n one of the earliest programs i n t, 2 G n i t e d States t o systematically investigate hydrogen-oxygen propellants for higbenergy rocket en3he application. Fran late in 1944 t o the cession of tests i n August 1949, tne hydrogen-oxygen programs at t h e Aerojet Gmeral Corporation, under t h e SponSGPShip of the Navy BL;reau of Aeronautics, a d m c e d these propellant.., f r o m theoretical performance studies t o practical sources of high specific impulse. thrust 4xu&ers, investigated the concept of ablative-cooled thrust chunbers, developed the first successfhl 1,000-lb-thst gaseous-propellant rocket engine, conducted t h e first tests of the effect of jet overexpansion and separation on performance of rocket Illustrative of t h e properties that make practical handling Specifically, t h i s work tested transpiration-cooled +Presented at t h e Fourth History Symposium of the 1nternat.iorx-1 kadderrly of wG.H. Osborn, Assistant, t o the Vice President, EngPieering <pe?ations, Aerojet Astronautics, Constaxe, G e m Federal Repkblic, OctQber 197C.

Acta Astronautica, 1992

Rocket propulsion, 2020

As rocket flies through the air, Aerodynamic Forces are generated and act on it. Forces are both magnitude and direction of vector quantities.

Newton's third Law of motion. It has a precisely shaped nozzle which helps to achieve high velocities of exiting fluid and thus more thrust. Most rocket engines use the combustion of fuels with oxidizer to produce hot gasses which are then expelled at high velocities and thus generating thrust. Some other types of rocket engines are also there in which highly pressurized gases is kept in a container and is expelled at high velocities to generate thrust. These rockets are also called cold gas thrusters. They mostly use inert gases stored at low temperature as their "propellant". Another type of rocket engines exists in which heat from nuclear reaction (typically, a fission reaction of liquid hydrogen) is used in place of heat from combustion of gases (as in a typical rocket) to heat liquid hydrogen and then expand it using nozzle to create thrust. These types of rockets are called Nuclear Thermal Rockets (NTRs). In this paper I will focus mainly on combustion-based rocket engines as they are the most commonly used rocket engines. Combustion-based rocket engines-Combustion based rocket engines are most commonly used in aerospace vehicles which are called rockets. Rockets carry their own fuel and oxidizer to feed the rocket engine and thus rocket engines can be, and are used for propulsion of the vehicle in vacuum of space. Another use of rocket engine is in ballistic missiles. Now, to start with, rocket engine has to basically do the job of combusting the fuel with oxidizer and expel gases at a high velocity. So, there are two types of combustion-based rocket engines-Liquid fuel rocket engines and solid fuel rocket engines (typically known as solid rocket boosters (SRBs)). As the name suggests liquid fuel rocket engines use liquid fuel and oxidizer to feed the nozzles, high temperature gas to generate thrust. On the other hand, solid rocket boosters use solid combustible compounds and oxidizers to produce hot gases for thrust. Some examples of fuels and oxidizers used in rocket engines are-Liquid hydrogen and Liquid oxygen; Kerosene (RP-1) and Liquid oxygen; Liquid oxygen and alcohol (ethanol); Liquid oxygen and gasoline; etc. for liquid fuel engines and, Charcoal and potassium nitrate; Aluminum powder and ammonium perchlorate; for solid-rocket boosters.

Vulcan, 2020

The article supplements and revises past historiographical explanations on why the US entered World War ii without propellant based engines, for tactical rockets and how that gap was overcome. Short range rockets were used extensively by all sides in the War for various purposes, but in the interwar period (1919-1939), rocket advances were made mostly in Europe with the US lagging behind. The rockets engines were based on solid propellant tubes, but in 1940 there was hardly any US tubes design knowledge and no production facilities. Technological and production gaps had to be closed, and from 1940 were made with a significant help from Britain and under the leadership of the civilian National Defense Research Council (ndrc) agency, merged in 1941 into the Office of Scientific Research and Development (osrd). Due to the pressing needs to equip American forces with rockets, a joint group of ndrc and Army developers modified in early 1942 an existing gun propellant production technology for rocket tubes. Used initially for the Bazooka this adoption was found later to be extremely problematic in production and performance of tubes in the widely-used, Army's 4.5inch barrage and fighter plane rockets. Working in parallel, a joint group of ndrc and navy developers was able to construct the more modern tube production process already used abroad, avoiding the main army difficulties and taking the lead. The growing needs for these superior Navy rockets, some of which were used extensively by the Army, led to gaps between supplies and demands by 1943. Two fortunate events, one of them connected with the Soviet Union, helped to relieve the shortage.

Revista Mexicana de Fisica

Elementary concepts from general physics and thermodynamics have been used to analyze rocket propulsion. Making some reasonable assumptions, an expression for the exit velocity of the gases is found. From that expression one can conclude what are the desired properties for a rocket fuel.

International Journal of Aerospace Engineering, 2012

52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016

International Journal For Multidisciplinary Research, 2024

This detailed research paper delves into the practicality and step-by-step process of creating a smallscale rocket and manufacturing its fuel from scratch within a home setting. The main objective of this study is to furnish a thorough manual for individuals passionate about amateur rocketry, emphasizing the importance of safety measures, materials, design concepts, and fuel composition. The project showcases the educational and experimental possibilities of rocketry in a domestic context, which can enhance knowledge of propulsion science and engineering fundamentals.