SPACE QUALIFICATION

Preparing the satellites for tough missions

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 in two configurations: individually and as an integrated CubeSat platform.

Our CubeSat platform underwent full campaign of tests at qualification level exceeding the standard requirements for this class of satellites

FUNCTIONAL TEST

Maintaining high performance level during the entire mission

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.

 

This flow chart shows the test sequence

Test Sequence Flow

Test sequence flow

PHYSICAL PROPERTIES

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

  • Momentum of Inertia (MoI): Fully assembled CubeSat platform

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THERMAL CYCLING AND THERMAL VACUUM TEST

Withstanding the high requirement of spaceflight

The purpose of the thermal cycling and 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 =40 °C.

  • Dwell Time = 2 h.

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The requirement for the TVAC test was vacuum conditions of 10-6 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 cycling and the thermal vacuum tests were performed in operating conditions as follow:

  • Vacuum between 10-5 and 10-6 mbar

  • Minimum temperature: -20 °C

  • Maximum temperature: 60 °C

  • Temperature variation rate ≥ 1 °C/min

  • Dwell time 2h at extreme levels

  • Number of cycles: 4

MECHANICAL TEST

Craftsmanship and resilience

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:

Sinusoidal vibration

  • Duration: sine sweep at 2 Oct/min, 5 Hz – 140 Hz;

  • Repetitions: 3 times for each orthogonal axes;

  • Qualification test level:

Frequency (Hz)

5-100

100-140

Amplitude (g)

2.5

1.25

Random vibration

  • Duration: 2 minutes for each test;

  • Repetitions: 3 times for each orthogonal axes;

  • Qualification test level

Frequency (Hz)

20

20-50

50-800

80-2000

2000

Overall

ASD level (g2/Hz)

0.026

+6dB/oct

0.16

-6dB/oct

0.026

14.1 Grms

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Shock Test

The shock test was performed using a proprietary pyroshock facility.

  • Repetitions: 3 times each for orthogonal axes;

  • Qualification test level

Frequency (Hz)

30

100

700

1000

1500

5000

10000

SRS (g)

5

100

1500

2400

4000

4000

2000