IRENE is a small re-entry platform intended for several applications including payload retrieval from LEO. It is equipped with a deployable, flexible aerobrake and allows low-cost short-notice missions.

In order to advance the TRL of this technology at a reasonable cost, a scaleddown flight demonstrator (MINI IRENE), fully representative of IRENE is proposed to be tested with help of a sounding rocket.

 

A successful Phase B of MINI IRENE has been recently completed with the construction and test of a ground demonstrator. The next step, objective of the present proposal, is to realize a flight hardware which will be tested in the frame of the DLR Mapheus sounding rocket mission for 2016 as piggyback payload.

 

 

The following activities have been implemented during the study:

 

• Interface analysis and adaptation of the capsule to the mechanical constraints.

• Mission analysis and thermomechanical analysis of the new configuration.

• Detailed design and construction of the critical components of the capsule:

• Dampers, Locking Mechanism, Release Mechanism.

• Interface with the rocket.

• Electronics (OBDH, Beacon, Sensors, Deployment of sensors and antenna, power supply).

• Surface treatments.

• Tests of the critical elements (rods, shock absorbers, fabric, elect. cards etc..):

• Deployment mechanism (functionality).

• Deployment activation mechanism.

• Aerobrake (aerodynamics and stability test).

• Fabric (Thermal and Mechanical test).

• Test or static loads on the aerobrake structure.

• Crash (drop test) dummy structural model.

• Electronics (test in vacuum).

• Delivery system and electronic activation.

• TLC (Tele-command)Test.

• Definition of the qualification testing of the entire capsule.

• Final design of the capsule and of all the subsystems.

• Construction of the capsule and of all the subsystems.

• Testing and qualification of all the subsystems:

• Vibration test on complete system.

• Functionality test (in thermo-vacuum conditions) of the system.

• Assembly, integration and qualification of the capsule.

• Delta qualification of the complete hardware on Scirocco plasma facility.

• Launch campaign, recovery and post-fligth data analysis.