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E-2 has successfully demonstrated a full mission duty cycle with margin, completing a 201 sec run at our Mojave, CA test site. Multiple 200+ sec test fires have now been completed, proving performance and reliability across engine builds. As the highest performance LOX/kerosene engine in the small launch class,...

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33,535 Aufrufe • vor 11 Monaten •via X (Twitter)

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E-2 making diamonds 💎💎💎 in the desert 🏜️ On September 15, 2025, our new engine unit completed its 6th test fire, a 202 sec full mission duty cycle with zero hardware issues. E-2 manufacturing and test cadence are accelerating.
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E-2 making diamonds 💎💎💎 in the desert 🏜️ On September 15, 2025, our new engine unit completed its 6th test fire, a 202 sec full mission duty cycle with zero hardware issues. E-2 manufacturing and test cadence are accelerating.

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At our Mojave, CA test site, E-2 ran at boosted thrust for a 1-minute duration, achieving 25,000 lbf thrust and measured 295 seconds Isp. Although E-2 is a kerosene/LOX engine, its plume is blue and transparent, demonstrating its 99%+ combustion efficiency. E-2 is now available for sale.
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At our Mojave, CA test site, E-2 ran at boosted thrust for a 1-minute duration, achieving 25,000 lbf thrust and measured 295 seconds Isp. Although E-2 is a kerosene/LOX engine, its plume is blue and transparent, demonstrating its 99%+ combustion efficiency. E-2 is now available for sale.

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Thirteen successful engine startups totaling 770 seconds of cumulative run time have been completed to date on the latest E-2 engine sample. Testing of this unit will continue to further characterize performance and extend the rated service life. E-2 is engineered to power spaceflight with rapid reusability and exceptional reliability at low cost. Propellants: LOX/Kerosene Thrust: 22k lbf (10 tf) Isp Sea Level: 290 s Isp Vacuum: 327 s Isp Vac Version: 365 s Cycle: Ox-Rich Staged Combustion
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Thirteen successful engine startups totaling 770 seconds of cumulative run time have been completed to date on the latest E-2 engine sample. Testing of this unit will continue to further characterize performance and extend the rated service life. E-2 is engineered to power spaceflight with rapid reusability and exceptional reliability at low cost. Propellants: LOX/Kerosene Thrust: 22k lbf (10 tf) Isp Sea Level: 290 s Isp Vacuum: 327 s Isp Vac Version: 365 s Cycle: Ox-Rich Staged Combustion

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Who has ever seen a LOX/Kerosene liquid 🚀 engine with a blue plume 💎💎💎💎? Not only does it look spectacular, but it also serves as undeniable proof of the 99%+ combustion efficiency achieved in this test. Enjoy this 3-minute, 20-second test of E-2, a mostly 3D-printed 22k lbf (10 tf) ORSC LOX/Kerosene liquid rocket engine. Nominal pressure: 100 bar; mixture ratio: 2.7. Recorded today at Stennis Space Center, this test also secured the duration record for the test stand. E-2 is now available for sale to launch companies.
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Who has ever seen a LOX/Kerosene liquid 🚀 engine with a blue plume 💎💎💎💎? Not only does it look spectacular, but it also serves as undeniable proof of the 99%+ combustion efficiency achieved in this test. Enjoy this 3-minute, 20-second test of E-2, a mostly 3D-printed 22k lbf (10 tf) ORSC LOX/Kerosene liquid rocket engine. Nominal pressure: 100 bar; mixture ratio: 2.7. Recorded today at Stennis Space Center, this test also secured the duration record for the test stand. E-2 is now available for sale to launch companies.

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Last week, we pushed our Hadfield MK IV engine and Darkhorse engine test cell to their limits ahead of our upcoming thrust vector control (TVC) and orbital engine test campaigns. It was thrilling to see this controlled test go sideways — literally! Orbital launch vehicles operate within narrow design margins and constrained safety factors, where excess mass in any subsystem directly impacts payload capacity or mission viability. Destructive and limit testing enable us to validate optimal mass-performance trade-offs across propulsion, pressure systems, and primary structures. Key outcomes from this test include: ✅ Structural margins validated – Darkhorse demonstrated stable operation under full thrust loads at gimbal angles exceeding design specifications ✅ Thermal performance characterized – Extended burn duration at off-nominal mixture ratios provided empirical data on regenerative cooling degradation modes and injector thermal limits ✅ Fault tolerance demonstrated – Engine maintained functionality despite progressive damage, validating robustness for anomalous flight conditions ✅ TVC readiness confirmed – Test results validate system integration for upcoming actuated TVC test series l Design optimization insights – Failure mode analysis generated actionable improvements for cooling architecture, injector design, thrust structures, and engine reusability At NordSpace, we push limits. Canada needs to get to orbit with sovereign light-lift launch by 2028 and medium-lift launch by the early 2030s. The only way this is possible is through extreme levels of testing, manufacturing, and investment. Our mission to build a Canadian end-to-end space missions capability will change the shape of our nation both on Earth and in space. If you would like to join our mission, please apply for a role at NordSpace via the Careers page on our website, and join us at the Canadian Space Launch Conference on May 5th, in Ottawa. National Defence Defence Research and Development Canada NSERC / CRSNG Canadian Space Agency Transport Canada
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