WARR: Cryosphere – Battleship Test Campaign

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 raketentechnik@warr.de

WARR 10kN Engine Test

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Hard work pays off!
On Friday we successfully fired our 10kN engine for 5 seconds. The system performed as planned as we nearly hit the nominal operation point. We are now looking forward to testing for the full burn time of 15 seconds next week.

WARR Hybrid Rocket Test

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 raketentechnik@warr.de

WARR: Cryosphere – Frigate Test 9 and 10

Video Caption: After several enhancements on our subscale engine, we lit it twice on the first of July. We hit the design point of the engine and collected valuable scientific data.
The now purely axial injection smoothens our combustion, just as predicted. Being able to safely predict the system behaviour is what we perceive to be the key to continue the development of successively larger engines.

More good news: The first hotfire test of the fullscale engine has now preliminarily been fixed to November this year – stay tuned!

Technical Data:
Mean thrust: ~1600 N
Chamber pressure: 20 bar
Burn time: 5 s
Mass flow oxygen: 550 g/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 raketentechnik@warr.de