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At EnduroSat we strongly believe in the endurance of our systems. Testing at the extremes and verifying the performance at the limit demonstrates the capabilities of our CubeSats. All modules are tested fully integrated in a 1.5U and 3U CubeSat platforms.

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EnduroSat performs the qualification test campaign of all its modules in the Space Qualification Laboratory of the Italian Aerospace Research Centre (CIRA).

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Functional Test

During the space qualification campaign, EnduroSat CubeSats underwent high level of functional tests to demonstrate the integrity of the system. All modules were performing at their nominal level.

The tests were performed following the strict specifications of the ESA ECSS-E-ST-10-03C and NASA GEVS: GSFC-STD-7000A standards.

Physical Properties

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Awareness of space environment Accurate determination of the physical properties:

• Weight: all subsystems (modules) and fully assembled CubeSat platform
• Center of Gravity (CoG): Fully assembled CubeSat platform
• Moment of Inertia (MoI): Fully assembled CubeSat platform

Thermal Cycling

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The purpose of thermal cycling test is to demonstrate that the systems are able to survive, without loss of integrity or functionality, the thermal loads experienced during the space mission.

• min Temp -30°C
• max Temp +65°C
• Temperature Variation rate ≥1°C/min
• dwell time 1h at extreme levels
• 8 cycles

Thermal Vacuum

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The purpose of thermal vacuum test (TVAC) is to demonstrate that the systems are able to survive, without loss of integrity or functionality, the thermal and pressure conditions experienced in the space environment. To reach deep vacuum conditions (as high as 10-7 mbar during the cold cycle), a bakeout of the systems was performed in order to minimize the outgassing during the TVAC test:

• Vacuum between 10-5 and 10-6 mbar
• Chamber Temperature =50 °C.
• Dwell Time = 2 h.

The requirement for the TVAC test was vacuum conditions of 10-7 mbar. EnduroSat systems were tested to even higher levels (10-7 mbar) in order to ensure their durability and performance. In accordance with the standards the thermal vacuum test was performed in operating conditions as follow:

• Vacuum between 10-6 and 10-7 mbar
• Minimum temperature: -30 °C
• Maximum temperature: 65 °C
• Temperature variation rate ≥ 1 °C/min
• Dwell time 1h at extreme levels
• Number of cycles: 8

Sinusoidal vibration

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The purpose of the mechanical tests is to demonstrate that the primary structure and all electronic and mechanical components can withstand the vibrations and the loads experienced during launch and deployment.

The tests were performed following the NASA GEVS: GSFC-STD-7000A standard:

• Duration: sine sweep at 2 Oct/min, 5 Hz – 140 Hz;
• Repetitions: 3 times for each orthogonal axes;
• Qualification test level:

Frequency (Hz)	Amplitude (g)
5-100	2.5
100-140	1.25

Random Vibration

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• Duration: 2 minutes for each test;
• Repetitions: 3 times for each orthogonal axes;
• Qualification test level

Frequency (Hz)	ASD level (g2/Hz)
20	0.026
20-50	+6dB/oct
50-800	0.16
80-2000	-6dB/oct
2000	0.026
Overall	14.1 Grms

Pyroshock Test

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The shock test was performed using a proprietary pyroshock facility.

• Repetitions: 3 times each for orthogonal axes;
• Qualification test level

Frequency (Hz)	SRS (g)
30	5
100	100
700	1500
1000	2400
1500	4000
5000	4000
10000	2000