The+Jig+V1.0

=**The Jig v1.-**=


 * Directions:** This is the page in which a record of what we have done will be shared. The rules regarding this are anything you change on somebody elses writing needs to be put in red so the original author can see. At the beginning and end of your work write your name in small font**.** If you used references please put them in, the page is about sharing of info**.** Later on this page will most likely be split into different sections so try to place apporpiate headers over your work**.** See my example below**:**

Nicholas Tegg

Oxidizer
After conducting research into the use of nitrous oxide as our oxidizer, the require pressure of the rocket engine was discovered. Nitrous oxide is stored as a liquid inside pressurised cylinders, to cause it to be a liquid at room temperature the pressure that it is under is 750psi or 5171kpa. As the liquid is released there is a pressure drop across the valve and expansion into the combustion chamber resulting in further pressure drop. Once the fuel and oxidizer reacte there is a further pressure drop. Research has shown the optimal pressure difference between oxidizer a chamber for a stable ignition and burn is 20%. Therefore since the maximum pressure is 750psi all the rocket engines components will need to be designed to withstand that stress. Nicholas Tegg

**Beginning**
The initial layout and type of rocket were decided. We are going with a hybrid rocket due to its simiplicity and being less dangerous than a solid rocket. Our fuels are parrafin wax and nitrous oxide which are stored seperately, one in a pressure vessel and the other in the combustion chamber. We are initially constructing a simple rocket motor to static test to give ourselves a thrust value for comparison as well as some proof of concept. I am mainly doing this first rocket motor by myself and it is not engineered very well since problems will be encountered and parts changed. The overall deisgn is a cylindrical pressure vessel which can hold 200grams of nitrous ozide which is then connected to a valve rated at over 750psi. This connects to the injector which is located on the entry side of the combustion chamber. The combustion chamber holds 50grams of parrafin wax with a hollow core to allow combustion and fluid flow. Following the fuel core is the main combustion chamber and the nozzle which also fits inside the cylinder. Both injector and nozzel will initially be made of steel and need to be fabricated in a lathe (we are looking at getting access to the motorsport/university workshop lathe, as well as a fellow students home lathe). The combustion chamber will be made from mild steel and will have a miniumum thickness of 1.5mm due to the pressure loading on it. The valve i am using is a nickel plated ball valve with a 10mm british standard thread connected to a 5/8-18 fiting a 20oz paintball gun cylinder. Below is a rough schematic of the design with a list of things needed.

Below is a sketch of the design that was manufactured during April including the nozzle which was designed by Tom. Feel free to discuss or comment if you want something explained.
 * . Version 1.1**

Drafted Parts
-These are the rocket and test rig parts that have been drafted to date. They are generally not to scale due to some dimensions being unknown and are drafted such that all important variables are changable, this should be done for ALL future draftings. They need to be drafted in NX 7.5-as the parts below are-which is available at university in the computer labs. Any questions regarding how to use NX 7.5 should be directed to one of the 4th yr students. (Nic, Tom, Louis)

Things we need
-money :) so far i have been buying everything out of my pocket -parrafin wax (candle wax) -someone to grind up aluminium cans and collecting the powder -most importantly nitrous oxide-to be sourced through the university

Things that need to be done
-project proposal . -licensing . -safety . -risk assessment . -competition . -etc -making parrafin core . -producing charcoal of fuel grain