The Nitrous oxide hybrid rocket engine will power the team’s Stratos IV rocket to over 100km, launching from South Africa in 2020.
Video Caption: The 20th test of the DHX-400 ‘Nimbus hybrid rocket engine. This is the first full-burn (38 seconds) test of the motor featuring in the configuration with a titanium composite nozzle!
Delft Aerospace Rocket Engineering is one of the largest and most advanced student rocketry teams in the world. As a Dreamteam of Delft University of Technology, we aim at providing students with a hands-on experience that is unique in this world. Next to our Stratos and Aether flagship projects, the DARE conducts fundamental research in all fields of sounding rocketry, such as propulsion, recovery, control, structural design and recovery.
Video Caption: During our tests the weekend of February 16th 2019 at MTA and FAR, we successfully tested our new Fuel and Liquid Oxygen tanks in two separate static fires. This video is of our second fire, using our newly built Thin-Walled Combustion Chamber. Due to a small issue in the building of this new combustion chamber, hot combustion gases built up in a small gap, causing the outward flames seen in the video. Thanks for watching and subscribe to see the launch of this Liquid-Propellant system in only a couple of weeks!
Video Caption: Over this past weekend of the 16th of February 2019, The Prometheus hybrid system successfully static fired at the FAR Facility! Thanks to their continuous hard work on their propulsion system, they got to see their engine light up the desert!
As per the tweet below, rescheduled by
two days to July 18th four days to July 20th.
Video Caption: The Stratos III launch campaign has started! Our first launch attempt is on July 18 2018 at 9.35 PM CEST. Live stream will be available at http://dare.tudelft.nl/live-stream/ and on ths channel!
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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
Video Caption: A student society that builds a record-breaking hybrid rocket engine powerful enough to lift an SUV? Check out the ninth engine test video. Unfortunately, 12 seconds into the burn an engine failure occurred.
Currently, it is believed the failure was caused due to an injector failure. It is hypothesised that the injector overheated due to an instability causing an increase in Oxidiser mass flow, which led to the chamber wall overheating and finally failing. A low and high-frequency oscillation event has been seen in the data and research to minimise these oscillations is being conducted. Our engineers are working hard on a forensic analysis to discover the cause and find a solution.
Due to our thorough safety procedures, no personnel were here harmed, however, one pumpkin was never seen again.
Video Caption: After two subsequent tests in July, we hot-fired the sub-scale engine again. Although we did not hit the design point of the engine due to feed system problems, we were able to collect valuable scientific data. Finding these problems in a sub-scale test enables us to implement a fix, before the start of full-scale testing. Technical Data: Mean thrust: 1255 N Design chamber pressure: 20 bar Burn time: 5 s Mean mass flow oxygen: 532 g/s ISP: 160 s
Please note: We’re predominantly master students of mechanical engineering and spend most of the time before test 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 firstname.lastname@example.org