On Tuesday the 10th of February, a Design Review session was held for the Stratos II+ Rocket to be launched in October 2015. Building upon the experiences gained in Spain during October 2014, the rocket incorporates changes to prevent the problems that were experienced. Below follows  a small summary from each sub-department:

Capsule Redesign

Martin Olde described several changes that were incorporated, particularly based upon input from the electronics team. These included:

• GoPro circuitry changes to allow better control of the cameras and prevent unintentionally starting to record that the current system is prone to.
• Telemetry Frequency  changes were made in accordance with the launch site, also freeing up space which can now be used for (among other things) better positioning of the flight data recorder.
• Pre-Flight Testing Programme. This would include mounting the capsule on a shaker table to validate the structure before launch. This would occur in both the up-and-down and sideways direction at a variation of forces and frequencies. It is intended that this would also be preformed with systems in the capsule turned on.

In addition to this, several smaller changes where also discussed. These were finer details like ‘cleaning up the capsule’ and some other layout changes. Considerable feedback was centered on the assembly of the capsule: sliding the fairing over the rest of the stack where there was a real risk of damage to parts.

Electronics Redesign

Geert Henk Visser talked about the changes to the electronics. Since these systems are well integrated with other systems, it requires coordinated change. Major points mentioned included:

• Engine Controller: Redesigning the circuit for two servos.
• FTS Antennas: Discussions of redesign to make them aerodynamically compatible with the body. Several solution were proposed and discussed; the best must be selected from these.

Propulsion System (Hybrids)

Ralph Huijsman spoke about the engine changes:

• N2O Seal: These would be changed from custom seals to industry standard seals. This has been possible due to the introduction of swivel pieces.
• Bad Accessibility of the Motor Bay: This has been entirely redesigned. It was now understood that the engine compartment may have to be open several times, which was never taken into account in the old design. The control compartment now has its own dedicated coupler/fairing for easy removal.
• CFD of the rocket: Is underway to analyse temperatures. The moment caused by any aerodynamic forces on external components was also discussed, such as protruding fairings.
• Engine Performance: A possible third test campaign will be conducted to increase confidence in engine performance. This would occur in June.

There was also work on the load cell inaccuracies, which we judged to have been caused by the very low nitrous oxide temperatures. The correct fin sizing was also discussed with the simulation team members. Subsystem design testing would occur in July. The evening was concluded with some drinks in the Korolev Lab.