Last week, we successfully tested the oxidizer tank of the N2ORTH rocket for the first time. The tank is a type V pressure vessel, which features a thin fluoropolymer surface coating on the inside to ensure nitrous oxide compatibility. The empty mass of the tank is only 16.8 Kg with a volume of 160 l and a nominal operating pressure of 75 bar. We are very satisfied with the result and are excited to see the behavior in the blow-down test.
HyEnD is proud to announce that it has tested its HyLIGHT-2 Engine in near-flight configuration for its full intended operation time of 25 seconds. The test was conducted at the test bench M11 of the German Aerospace Center in Lampoldshausen and marks a big milestone for the development of the N2ORTH rocket.
The tested configuration has a dry mass of 13.5 kg and was loaded with 20 kg HTPB-based fuel. In addition, 2 kg of HDPE are located in the post combustion chamber in order to function as a film cooling ablator for the nozzle section. The multi-element swirl injector and graphite mixer in the post combustion chamber ensured a high reaction and overall engine efficiency, resulting in a specific impulse at sea level of 224 seconds. Operating at 30 bar chamber pressure and an oxidizer to fuel ratio of 6.07, an overall impulse of 267064 Ns was achieved.
The next test with minor optimizations of the design is scheduled for end of March. This test will be the final static test and will qualify the engine design. For April and May, integrated tests in blow-down configuration together with the rockets oxidizer tank, fluid system and ground support equipment are planned.
Take a look at the video of the test:
On Saturday, our self-developed and self-sewn ribbon parachute was tested for the first time. The parachute is designed for an operation point with low air density and high descent rates. Its main task is to slow down the fall of the rocket from supersonic to a sufficiently low speed to ensure a safe release of the main parachute. For this first test, we have built a small version of our drogue chute to familiarize ourselves with the manufacturing and testing procedures. After evaluating the test, we will design and build the bigger version for our rocket N2ORTH.
HyEnD is proud to announce that the first 15 s test firing of its lightweight engine HyLIGHT-2 with CFRP-casing was a success! In the upcoming weeks, the operation time will be increased to 25s. The test was conducted at the test bench M11 of the DLR Institute of Space Propulsion. Thanks to all who made this achievement possible!
Please note that the video is only available in German.
Im Juli des vergangenen Jahres hat uns Mo vom YouTube-Kanal Senkrechtstarter besucht. Wir haben uns sehr gefreut einige Einblicke in die Arbeiten im Rahmen des aktuellen DLR STERN Projekts geben zu können. Unter anderem zeigen wir verschiedene Komponenten der Compass-Rakete und mischen mit Mo den Brennstoff für unsere Hybridtriebwerke an. Das Video ist nun auf dem Kanal Senkrechtstarter verfügbar – danke für deinen Besuch, Mo!
On 9th September 2021, HyEnD has successfully tested its HyLIGHT 10kN rocket engine for the first time. In contrast to the planned flight version of the HyLIGHT engine, the prototype engine tested features an aluminum casing. This allows a modular engine design and a reuse of insulation components in multiple test configurations. The first test was conducted with an impingement injector and film cooling ablator in the post combustion chamber. The burn time of the engine was restricted to five seconds, as the goal of the test was to prove that all required systems are working correctly and reliably.
The current test campaign will assess the effectiveness of film cooling and the influence of various design changes to the combustion efficiency. The regression rate will be evaluated and optimized as well. Since September, various prototypes of the engine have reached a culminated operation time of more than 37 seconds. In the following weeks and months, the design of the fuel grain, injector and insulation components will be finalized, and the burn time increased to up to 25 seconds. First tests with an engine with CFRP casing are planned for early 2022.
Update from January 2022: We now have conducted a total number of 7 hot fire tests within the HyLIGHT-1 test campaign. Some impressions from the tests are summarized in the following video:
On 25 June 2021, HyEnD successfully launched its subscale demonstator rocket „Compass“ for the DLR STERN project. The launch took place at the Truppenuebungsplatz (military training area) Heuberg. Compass was able to reach an altitude of more than 3200 m / 10,000 ft above ground and an initial accelleration of more than 6.5 g. During ascent, all systems performed nominally. Drogue and main parachutes were ejected– however, the main parachute was not able to unfold, and the rocket landed with a descent rate of about 20 m/s. This resulted in some damage to structural components and the fluid system. We want to thank all supporters that have made this launch possible! Scroll down for more pictures of the launch.
At the beginning of May, the drop test of the Compass recovery system took place. At an altitude of 500m, a dummy with the dry mass of Compass was dropped out of a model aircraft. The drogue chute decelerated the dummy down to 26 m/s and the main chute to 3.3 m/s. The parachutes had already been tested in the IAG wind tunnel and the drogue parachute ejection system had been tested on ground a few weeks ago. The aim of this overall test was to verify the forces that occur in the simulation and to ensure that Compass can be recovered safely.
HyEnD has successfully conducted the Static Hot Fire Test of the Compass Demonstrator Rocket. Engine, tank, fluid system and ground support equipment were tested together. The test has shown that remote tanking and launching of the rocket works safely and reliably – we are looking forward to the launch.
On March 24th, 2021 HyEnD has tested its first rocket engine with a carbon fiber reinforced plastic (CFRP) casing. The casing consists of multiple layers of carbon fiber and is produced on our winding machine in our facilities at the MPA Stuttgart. This marks a big milestone in our STERN project participation, since the new, lightweight casing was one of the most ambitious goals of the project.
The resulting engine has a dry mass of only 0.95kg and can handle pressures of up to 100 bar / 1450 psi. Tests have shown stable and efficient combustion with a measured specific impulse of more than 210s.