1. Solar Probe Plus FIELDS V1234 Mechanical Pre-Ship Review May 26, 2017
DRAFT
David Glaser
FIELDS Mechanical Engineer
Space Sciences Lab
University of California, Berkeley

2. Evidence of Acceptance by Developer QA
Assembly of V1, V2, V3, and V4 Flight instruments completed
See As-Built Flight Assembly Procedures
V1234 passed Acceptance Vibration Tests –
See SPF_ANT_070_RevE_V12_FM_Vibe_As-Run_Signed.pdf
See SPF_ANT_070_RevF_V34_FM_Vibe As-Run_Signed.pdf

3. 1. Storage and Integration Requirements
Storage of the V1234 instruments requires ESD safety precautions. A connector saver will be on the preamp harness connector. The end of the whip clamp will have a short length of whip tubing, which must be grounded at all times. The instrument does not require purging or an inert atmosphere.
The reference document SPF-ANT-PRC-021 V1234 Integration Procedure contains instructions for integration (incorporated into APL integration procedure)
The reference documents SPF-ANT-ICD-001 V1 Antenna MICD, SPF-ANT-ICD-002 V2 Antenna MICD, SPF-ANT-ICD-003 V3 Antenna MICD, SPF-ANT-ICD-004 V4 Antenna MICD contains all relevant mechanical interface data.
The most vulnerable parts of the V1234 instruments are the two small antennas are the thermal shield, the white painted areas, which are no-touch surfaces, and the whip end of the stub, which must be grounded at all times.
Prior to I&T, the instrument will be stored mounted to bench fixtures, on a flow bench in the clean room.
During I&T, when on the spacecraft, the V1234 instruments will almost always have their covers on.
During I&T, red tag covers will only be removed for deployment tests and for observatory TVAC and EMC tests.

4. V1234 PSR Reference Documents (PDF)
T8itle
Document Number 1
V1234 Indentured Drawings List
SPF_ANT_IDL_ 001 Rev E 2
All drawings from IDL
V1234 FM Part Drawings 3
As-Built Assembly Procedures
SPF_ANT_PRC_ , 017, 019, 020, 021 4
V12 FM Vibe Test Procedure As-Run
SPF ANT 070 Rev E As-Run 5
V34 FM Vibe Test Procedure As-Run
SPF ANT 070 Rev F As-Run 6
V1234 Integration Procedure
SPF_ANT_PRC_021 7
V1234 MICD
SPF_ANT_ICD_001, 002, 003, 004

5. Final Configuration Photographs
Additional Photographs of the flight hardware are located at:

6. V1 Final Configuration Photographs
Additional Photographs of the flight hardware are located at:

7. V2 Final Configuration Photographs
Additional Photographs of the flight hardware are located at:

8. V3 Final Configuration Photographs
Additional Photographs of the flight hardware are located at:

9. V4 Final Configuration Photographs
Additional Photographs of the flight hardware are located at:

10. Final Configuration Photographs – Red Tag Cover
Additional Photographs of the flight hardware are located at:

11. Final Configuration Photographs - Underside
Additional Photographs of the flight hardware are located at:

12. V1234 Acceptance Vibration Testing
Note: There are 30 test graphs in the report. Only a representative sample of the data is presented here

13. Testing Summary
Acceptance vibration tests performed per the requirements of
_Rev_D_EDTRD_1108_Clean
Addendum s from Shelly Conkey
Two antennas were tested at a time
Random tests were notched around the first 3-4 modes of the thermal shields
Triaxial Accelerometers were mounted as shown (selective channels used)
Input Grms not to be more than 10% below un-notched spectrum
Minimum acceleration (G2/Hz) not to be more than 14 dB below un-notched spectrum
Pre- and post-test sine surveys performed
Comparison Plots Generated to identify structural changes

14. Accelerometers Principal Concern: Shield behavior
Radiator
Underside
Stub
Clamp
Shield
Principal Concern: Shield behavior
All triax, but only selective channels used – focused on X and Y axes
X-axis test Shield accel removed for 0 dB Random
Stub accel proxy for shield accel
Y and Z axes Shield accel left on
Radiator accel provided indication of overall antenna integrity

15. FIELDS Acceptance Sine Vibration
EDTRD Test Levels
FIELDS Acceptance Sine Vibration
Frequency
X , Y, and Z Axes
(Hz)
(g) 5
1.0 37 47
20.1 50 60
100
Sweep Rate: 4 oct/min
Sine Test Levels
FREQ(Hz)
ASD(G2/Hz)
20.00
0.0028
35.00
0.15
60.00
70.00
0.023
200.00
250.00
0.23
600.00
0.0062
12.49 Grms
1 min/axis
Random Test Levels

16. X-axis Configuration

17. Y-axis Configuration

18. Z-axis Configuration

19. V2 X-axis Sine Signature Pre and Post-Sine
V2 Pre-Sine
Changes in amplitude, and sometimes frequency, of the shield-stub, are normal
Overlaying pre-and post- graphs is not too useful
V2 Post-Sine

20. V1 & V2 X-Axis Notching Frequencies
V1 Post-Sine
Notching frequencies chosen from the combined min and max of both antennas
V2 Post-Sine
Notch
93-153Hz

21. Notching Frequencies Summary (All Antennas)
V1 & V2
V3 & V4
X notch Hz Hz
Y notch Hz Hz
Z notch Hz Hz

22. V1 & V2 X-axis Random Notching from 93-153 Hz Input Grms -14 dB Line

23. V2 X-axis Sine Signature Pre & Post-Random
No shield accelerometer

24. V2 Sine Signature Modes Summary

25. Random Input Grms Summary
Un-notched input spectrum: Grms
Requirement: No more than 10% less: >11.24 Grms
All inputs well within requirement
Axis
Prescribed Input with notch (Grms)
As-Run Input with notch (Grms)
Difference from un-notched input
Notch > -14 dB?
V12 X
12.42
12.29
-2%
Yes
V12 Y
12.44
12.36
-1%
V12 Z
12.43
12.35
V34 X
V34 Y
12.38 (V3)
12.44 (V4) 0%
V34 Z
12.40
-<1%

26. Post-Test Hardware Inspections
Accessible Screws Tight
No discernible damage to instrument
No cracks seen in bulkhead welds
Passed Inspection V1
Yes V2 V3 V4

27. V1234 Acceptance Vibration Conclusions
Pre- and post- frequency shifts meet requirements
Random input levels meet requirements
Post-inspection revealed no loose hardware, no damaged hardware, or any other anomalies
All antennas passed the acceptance vibration test