Carl from Brittish Reaction Research has posted a new update on his rocket engine project and is looking for some guidance on his heat transfer calculations.
This post is going to deal with some tentative calculations on the quantity of heat transferred through the walls of a rocket nozzle I am building. This study is part of my ongoing engine project. To be more specific, I’m interested in finding out how much coolant flow will be required to safely absorb the heat generated by the combustion gases.
Carl runs through the series of calculations required in detail which can be found here, worth a read, it is really easy to follow and if you can help him out, do so!
If you have got this far, thank you for staying with it. Perhaps now you would allow me one last indulgence and tell me if you think I have got it somewhere near right!
Help out a fellow amateur rocket engineer!
[Source: Copenhagen Suborbital’s ]
The Nexø II rocket remains grounded on land until summer of 2018, the board of Copenhagen Suborbitals has just decided.
Launching a rocket is a large-scale project. A lot of different parameters must be fulfilled in order for the Nexø II mission to be optimum, and this year it has simply not been possible due to both internal and external delays combined with bad weather conditions.
Next week was our last launch window but one of our stakeholders was not able to be there
during the launch and we couldn’t get the airspace cleared.
That’s why we have now finally decided to exercise due diligence around the project, hence postponing the launch of Nexø II for weather conditions again to be favorable.
The mission is still on, and we are launching Nexø II in the summer of 2018.
Until then, you can see the Nexø II rocket in the Copenhagen Suborbitals headquarter at Refshaleøen in Copenhagen.
Disappointing to read this, and is not the first time this has happened, Nexø I was delayed from 2015 to 2016. Being constrained to one season of the year with an ocean-based launch infrastructure does not really help the flight rate.
I do not doubt the team’s long-term commitment to putting a person into space but the pace will have to change to keep the general public interested for the long haul.
The below tweets sum it up. ( AA is/was Armadillo Aerospace)
A nice overview video of USCRPL’s Fathom II launch from back in March showcasing prep, launch/flight, and recovery. The team set a record for student built rockets.
Video Caption: On March 3rd, 2017, University of Southern California Rocket Propulsion Lab launched Fathom II, a sub-scale model of its space-shot vehicle in Spaceport America, New Mexico. Fathom II reached 144,00 ft at apogee, taking the record for highest student rocket by almost 50,000 feet.
This deserved a post on its own.
I found a couple more video’s of this 3D printed aerospike online which go into a bit more detail.
Of note, the engine has multiple internal chambers, which in the future could be used for thrust vector control, as well as the regen cooled chamber, the spike is also cooled. The engine burns Methane and Gaseous Oxygen producing a thrust of 4kN or 1000lbf, the video below shows a burn time of 60sec.
More info on the project can be found here and here.