The spacecraft and its subsystems and components shall not be susceptible to emissions that could adversely affect their safety and performance.
This will prevent adverse affects from EMI/EMC during launch and on orbit operations.
Test requirements are derived from GEVS-SE. Levels may be modified to meet mission unique requirements.
The EMI/EMC requirement shall be satisfied by the following tests at the component, subsystem, and spacecraft level of assembly.
EMC Tests Per Level of Assembly
Type Test Description GEVS-SE C S/I P Levels
Para. No.
CE01/03 DC Power Leads 2.5.2.1a&b X X Fig. _ & _
RE04 AC Magnetic Field 2.5.2.2b X X X Fig. _
RE02 E-Fields 2.5.2.2c&d X X X Fig. _ & _
CS01/02 Power Line 2.5.3.1a X X Note 1 & 2
CS06 Power Line 2.5.3.1e X X Note 3
Transients
RS03 2.5.3.2a X X X Note 4
E-Field (Gen. Comp.)
Note 1: AC sinusoidal ripple shall be applied to primary power input bus to produce a differential voltage of the test sample input power connector of 7.92 V p-p (2.8 Vrms) from 30 Hz to 1500 Hz then decreasing linearly to 2.83 V p-p (1.0 Vrms) at 50 kHz.
Note 2: AC sinusoidal ripple shall be applied to primary power input bus to produce a differential input voltage at the power connector of 1.0 Vrms from 50 kHz to 400 MHz. The input ripple shall be swept over the frequency range at a rate not to exceed 1 decade per minute while monitoring the performance. 50% 1 kHz square wave modulation should be added with project approval.
Note 3: The test item is to be operated at the nominal supply voltage of +28 V. The item shall operate while input power lines are injected with the voltage transient described (shown in figure 6). The transient shall be superimposed on the power line voltage and be applied for 5 minutes at a repetition rate of 60 pps. The voltage transients shall be applied differentially between positive and return power leads with both positive and negative polarities.
Note 4: 2 V/m over the frequency range of 14 kHz to 2 Hz; 5 V/m over the frequency range of 2 to 12 G Hz; and 10 V/m over the frequency range of 12 to 18 G Hz (only to spacecraft with a Ku band telemetry system). Amplitude modulate the signal with a 1 kHz square wave (50% modulation)
Revision: August 25, 1995