The rocket consists of the following subsystems:
- Nosecone Section (incl. flight computer)
- Active Stabilisation Section
- Recovery Section (i.e. parachute deployment device)
- Instrumentation Section (i.e. Inertial Measurement Unit + Sun Sensor)
- Propulsion Section (shell structure)
- Engine Section (DXS Asimov)
Nose Cone Section: Flight Computer
The nose cone of the Aether launcher houses the brain of the rocket, namely the flight computer, which is designed by the Electronics Team and ACT and is based on the DARE General Flight Electronics.
The Aether Flight Electronics consists of the following items:
- Battery Pack
- Power supply board
- Main processor board, including ACT software
- Actuation board for actuators
- Sensor board
- Telemetry board
Active Stabilisation Section
After having successfully tested the Stability Augmentation System of the CanSat V7S developed by the Advanced Control Team, the team is upscaling the canard system for supersonic speeds. Project Aether is the first DARE rocket which features supersonic active stabilisation.
The canard system is mechanically limited to do roll-stabilization only because the ACT still needs to test full control on a small scale. Via an integrated gearing system, the canards will always rotate into the same direction, which improves the safety of this system.
The Aerodynamics department within the ACT is performing dedicated Computational Fluid Dynamics (CFD) simulations, to study the flow of the canards in supersonic speeds and to optimise the design.
The recovery system is a concepts that aims to solve difficulties present in the
Stratos II+ recovery system. It uses a drogue parachute deployed by a high-speed cold-gas parachute deployment device (PDD), which gives it a wider design envelope than the system used for Stratos II+. In addition, it solves much of the multibody dynamics, which are notoriously difficult.
The drogue chute will be deployed at high velocities, and is connected to the bottom of the rocket in such a manner, that it will turn the rocket into a flat spin. By doing so, the rockets’ velocity will decrease even more, and results in a stable descent.
The Instrumentation Section houses the main sensor of the Aether control system, the XSENS Inertial Measurement Unit (IMU). This sensor is able to measure the attitude of the rocket during flight, which is an input for the flight control algorithms to actuate the canards. The location of the IMU is at the Instrumentation Section, such that it is closer to the center of gravity of the rocket.
A second sensor which is placed in the Instrumentation Section is the LENS BiSon64 Sun Sensor. The team is investigating if this sensor can be used to determine the attitude of the rocket for the control algorithms.
Additional components which will be installed in this section are cameras, and a data connection cable to monitor the entire state of the rocket during count down.
The propulsion section is the casing around the engine, which includes attachments for the bottom fins. This part of the rocket will be made completely out of composites, which makes it the first large rocket within DARE which extensively uses composite materials.
The Capsule & Recovery Team is investigating techniques to make the propulsion section completely out of composite material including the fins, which brings challenges when it comes to attaching composite fins to composite tube. Cleaver methods such as using local integrated aluminum reinforcement rings are considered as a feasible solution to guarantee a solid connection between the fins and tube, to cope with the aerodynamic loads acting on the fins.
The propulsion section allows to easily slide the DXS-Asimov solid engine into it, which facilitates the assembling process during the launch campaign. Via the modular connection interfaces, the top part of the rocket is attached to the propulsion section.
To ensure that Aether will lift-off and reaches supersonic velocity, the rocket is powered by the biggest solid rocket motor ever developed by DARE: the DXS-Asimov. The DXS-Asimov is derived from the Leonidas 5 engine, the previous large engine of the Solid Propulsion Team. To ensure that the engine meets its theoretical performance, various single grain motor (SGM) tests and full-scale motor (FSM) tests are conducted during the Aether development process.