PEASSS Flight Model

The Breadboard phase has come to a successful conclusion with the vibration test for qualification of the PEASSS Nano-Satellite EQM Model.
Following this successful conclusion the consortium started manufacturing the components for the Flight Model (FM). On the pictures below the components of both the satellite and the payloads are shown.

Figure 1, Flight Model of the pyroelectric power generator consisting of two sets of piezo elements covered with black foil for optimal heat transfer

Figure 2, frontside of the FM Optical Bench with the two sun sensors visible. The right sun sensor mounted on the gimbaled ring-disc structure that can be tilted by the two piezo bimorph actuators that are located at the backside.

Figure 3, backside of the FM Optical Bench with the two piezo bimorph actuators visible that can tilt the sun sensor on the gimbaled ring-disc structure. On the backside are also the optical fibers with the Fiber Bragg Gratings (FBG’s) located.

Figure 4, Flight Model of the interrogator mounted on the electronics plate between high voltage amplifiers. The components are mounted in a test frame.

Figure 5, solar panels of the PEASSS satellite

All these Flight Model components have been individually functional tested and have past all success criteria. In this phase the development of the software both for the satellite platform and for the payloads was also started.
After the manufacturing phase, the assembly of the components was started. The development of the software continued, followed by extensive testing.


Figure 6, 'flat sat' testing before mechanical integration

Then  after successful testing of the software the integration was performed. Finally after integration the environmental testing of the Nano-Satellite was started.

Figure 7, integration of the payload into the PEASSS satellite structure.

The top panel of the satellite is the Smart Structure where a sun sensor can be pointed by means of two piezo beams. Both the tilting sun sensor and a second sun sensor which is used for reference are protected by a black cover with PEASSS inscription.

Figure 8, The fully integrated PEASSS satellite in a thermal chamber for the “thermal bake-out” as required by the launcher

Figure 9, The PEASSS satellite mounted in a test pod on the shaker for vibration testing

The testing of the Flight Model consisted of functional testing of the integrated satellite and environmental tests.
The functional testing of the satellite is performed before and after every environmental test to ensure that nothing has changed during the test. The environmental tests are a vibration test at proto-flight level, a shock test at prototype level and a thermal bake-out as required by the launcher

Figure 10, The Flight Model of the PEASSS satellite before integration in the launch-pod