. #Detail of the #RaptorEngine which will be used in BFR – Big Fucking Rocket. 31 of these bad boys will create a monster thrust of 29,000,000 lbs (~129,000 kN) and will push the BFR to the space. For comparison, recent Falcon Heavy launch recorded a total thrust 5,000,000 lbs (~23,000 kN). Now you know. Come on, iťs not rocket science…….or is it 🚀🎓 . . . More info on the BFR rocket and the ITS – Interplanetary Transport System – coming soon. Stay tuned! . . . #starman #starmanbyspacex #raptorengine #bfr #bigfuckingrocket #rocketscience #dnesletim #rocketlaunch #its #iauconference #interplanetarytransportsystem #motor #followme #spacexploration #spacex #engineering #technology #sosa
Video Cation: After 4 years of development, WARR performed the first hotfire tests of Europe’s most powerful cryogenic hybrid rocket engine. With 3kg/s of liquid oxygen massflow, the “Battleship” generates 10kN thrust for up to 15 seconds burn time. The design point of 20bar chamber pressure was nearly hit and valuable performance data was collected for further improvements. The two-week campaign included verification coldflows, ignition checks and four hotfire tests with 5s, 10s (2x) and 15s burn time.
Special thanks to all members of the WARR Ex-3 Project as well as the members of the M11 Test facility at the German Aerospace Center (DLR) Lampoldshausen for the support and guidance. This project was funded by the Federal Ministry for Economic Affairs and Energy (BMWi) during the STERN Project.
Please note: We are predominantly master students of mechanical & aerospace engineering and spend most of the time before tests on calculations and preparations to prevent severe damages on material and personnel. Please don’t feel inspired to light your own rocket motor in your backyard. Rocket science is a serious issue – if you get the numbers wrong, people die. You have some experience in mechanical/electrical engineering and want to participate, become part of the team? Feel free to send your application to email@example.com
Well, what a weekend it has been, both Purdue SEDS and the SDSU Rocket Project conducted successful tests of their own respective LOX/LCH4 rocket engines or methalox engines as they are sometimes called.
Both teams intend to fly these rocket engines in the FAR-MARS prize in May and therefore are eligible to win up to $100k of prize money!
Awesome work being done by both and great to see liquid methane being given a go by student teams.
A great easy to follow video from CS for those not familiar with how a liquid-fueled rocket engine works.
Video Caption: This video describes how the regeneratively cooled LOX / Ethanol engine used in the HEAT-2X rocket works.
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Ignition! The teams first monolithic finocyl motor set team records for highest thrust and highest efficiency, peaking at 6800 N of thrust and 224.2 s of isp.
The team is really pushing forward with their work on solid rocket motors, great to see so many frequent tests on variously sized motors.
I expect to see good things at this rate of progress!
Pc: 816 PSI (5.6 MPa)
Thrust (max): 5221 N (1173.7 lbf)