Table 2.

Test strategy for SCCT validation and acceptance, including description and rationale per model, except for the EM (no environmental tests)

Test type	Test	Description	Rationale	Models
Dynamics	Sine survey	Low intensity sine vibration up to 2500 Hz	Validation of the hardware natural resonances. Executed before and after each test to monitor the SCCT health.	ETU EQM FM-FS
	Quasistatic loads	Five low-frequency vibration of 72 g bursts.	Verify the survival of the hardware to low-frequency loads received during launch and/or landing.	EQM
	Random vibration	Vibration with a determined frequency response simulating the flight vibration.	Verify the survival of the hardware to the highest loads to be supported by the hardware during flight.	EQM FM-FS
	Shock test	Two three-axis shocks with short decay time. Risk-mitigation: 2000 and 4000 g. Qualification: 3500 g.	Verify the survival of the hardware to the shock produced by pyrotechnic devices to deploy the rover wheels during landing.	ETU EQM
Thermal tests	Thermal Vacuum	Temperature cycling in vacuum (10−5 Torr). Qualification: 29 cycles between −135 and 80 °C. Acceptance: 2 cycles between −135 and 70 °C.	Verify the survival of the hardware to the thermal stress produced during cruise and Mars day/night cycles. Acceptance test is shorter to avoid over-stressing the flight hardware.	EQM FM-FS
	Mars pressure	One temperature cycling in Mars pressure conditions (6 mbar of N2). Qualification: between −135 and 80 °C. Acceptance: −135 and 70 °C.	Verify the survival of the hardware to the thermal stress in Martian conditions. Test the effect of entry in Mars atmosphere on the hardware due to gas thermal inertia or potential thermal conduction effects.	EQM FM-FS