Project Update

N₂ORTH Propulsion System Test in Blow-Down Operation

The N₂ORTH propulsion system was successfully qualified in a hot fire test for a propellant throughput of more than 100 kg on August 25th. This marks an important milestone for the project, as HyEnD now has a flight-worthy propulsion system for the launch.

The fluid system of the ground support system (GSE) was used in order to fill the oxidizer tank with nitrous oxide and helium. The GSE includes two intermediate tanks for storage of the required amount of nitrous oxide for the filling process as well as a remote filling arm with a quick disconnect coupling.

The test setup includes the valves of the rocket as well as additional valves that are controlled using the test bench. An overview of the setup can be found below:

During the test, the rocket’s oxidizer tank was operated in a blow-down configuration together with the fluid system and engine of the rocket. The hot fire of the engine included the main operation phase of the engine and also the gas blow down after the depletion of liquid oxidizer, resulting in an overall hot fire duration of more than 50s.

In the upcoming weeks, the team will prepare another test with increased propellant mass in order to unlock the full potential of N2ORTH.

Project Update

Recovery Tests at IFT

As the launch of N2ORTH is getting closer, last validation tests of the recovery system are performed before final assembly. In mid-July a drop test was performed to verify the mechanical integrity of several recovery components.
The experimental setup is based on a drop test bench where a drop weight can be lifted up to 7m. At the end of the fall length, an impact plate transmits the energy of the falling weight into the connected recovery components. By applying a dynamic load equal to the opening shocks during main chute deployment, the recovery mount to the rocket’s hull structure was tested. All components withstood the required design loads over several load cycles without substantial damage.
Furthermore, the modification of the shock absorber was determined by these tests.
We want to thank the Institute of Mechanical Handling and Logistics for the technical support with the drop test bench.

Project Update

N₂ORTH Integration and Alignment Process

HyEnD has started the integration process of its N2ORTH rocket for the launch in Esrange later this year. One of the most crucial aspects of the rocket assembly is to ensure precise alignment of the components. Every slight deviation can have an influence on the flight trajectory and has to be considered in the mission analysis.

We achieve alignment by using a laser beam and photogrammetric measurements: First, the laser beam is aimed over a notch in order to align it with the tank axis, which was determined in a previous process. For the next step, the tube connector is inserted partially into a segment of rocket structure. Two targets are placed onto the structure segment aligned with its axis. The targets consist of grids perpendicular to said axis. After that, the structure segment can be aligned to the tank axis. Alignment is achieved when the laser beam intersects the two grids at the same point. Next, the tube connector is connected to the tank with a small amount of epoxy.

In order to evaluate the alignment, photogrammetry is used. This method generates point clouds to which cylinders can be fitted using CAD software. The offset and angle between the different parts then can be analyzed. Different plausibility checks are performed in order to ensure that the obtained measurements are viable.

Project Update

Compass Rocket Paper now Available

In June, HyEnD had the honor to present a paper at the 2nd International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR 2022) in Heilbronn. The paper discusses the overall design and key technologies of our demonstrator rocket Compass. Insights in the design of the oxidizer tank, hybrid engine, pyrotechnical valves, recovery system and avionics are given. The paper is now available on ResearchGate.

Project Update

HyLIGHT Engine Tested at Elevated Thrust Levels

Great news from the propulsion team. After the engine was tested successfully for a total impulse of 267 kNs in March at the 10kN thrust level, HyEnD encountered problems regarding combustion instability and high frequency oscillations at elevated thrust levels. 
As the rocket is operated in blow-down mode, the thrust continuously decreases during operation. Elevated initial thrust levels are necessary in order to ensure a sufficient initial acceleration when the rocket still contains its maximum propellant load.
After multiple short duration test firings in June and July, the design of the engine was optimized and now allows for stable, smooth, and efficient operation at thrust levels of up to 15kN. At 40 bar chamber pressure, a specific impulse of more than 230s was achieved. In the upcoming weeks, the entire propulsion system will go through final testing as the launch is getting closer and closer.

Project Update

Flight version of drogue parachute tested

Great news from our supersonic drogue parachute! After evaluating the first test of our supersonic ribbon parachute, we not only improved the shape and design, but also the manufacturing and testing process. Three months later, we were finally able to test the flight version of the self-sewn parachute at Würth Airport in Schwäbisch Hall. We are now looking forward to testing the entire sequence of the recovery system.bWe would like to take this opportunity to thank Adolf Würth Airport GmbH for the use of the runway and the AMANN Group for providing the sewing yarns.

Project Update

N2ORTH Oxidizer Tank Successfully Tested

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.

Project Update

HyLIGHT-2 Engine Tested for 25s

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:

Project Update

Drogue Parachute Tests

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.

Project Update

First HyLIGHT-2 Test with CFRP Casing

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!