Photographs

Spacecraft Charge Monitor

(From Home)

Spacecraft Charge Monitor (SCM)

(From NASA Final Report: Cover Page)

Figure 2.1.03: SCM sensor head (hemispherical analyzer)

(From NASA Final Report: Development of the SCM: Pre-Phase II Development )

Figure 2.1.04: Electronics for Phase I

(From NASA Final Report: Development of the SCM: Pre-Phase II Development )

Figure 2.2.04: Custom designed, low profile, rugged CEM for the SCM

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.05: SCM part being machined

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.06: Examples of internal parts for the SCM

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.07 : Unpotted 5kV DC-DC converter

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.12: Plastic 'see-through' mock-up of SCM electronics housing

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.13: View of the SCM during assembly

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.14: View of the SCM during assembly

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.15: Complete SCM

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 3.3.03: SCM on JHU/APL 'small shaker' for vibration tests

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.3.04: 5MHz crystal oscillator disassembled

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.3.05: Solid state retrofit in old package

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.3.06: Potted unit

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.3.07: The FPGA shook loose during its third 9-minute shake at 14.5 Gs

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.3.08: Board conformally coated

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.4.02: Thermal blanket over SCM

(From NASA Final Report: Tests of the SCM: Thermal-Vacuum Tests)

Figure 4.0.01: The flight-qualified SCM weighs 650 grams (<1½ pounds)

(From NASA Final Report: SCM Flight Prototype Specifications)

Figure A.01: Complete flight prototype Spacecraft Charge Monitor

(From NASA Final Report: Appendix)

Figure A.02: SCM and basic test apparatus for this project

(From NASA Final Report: Appendix)

Figure A.09: Photo of Beam Shield

(From NASA Final Report: Appendix)

Goembel Instruments laboratory

(From Home)

Vacuum chamber and electron optics controls

(From Facilities)

Electron gun

(From Facilities)

Figure 2.2.01: Dual turbo-pumped vacuum chamber

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.02: Assembly of our unique electron gun

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.03: High performance electron gun.

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure and 2.2.08: Vacuum potting process at Goembel Instruments

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 3.1.01: Full chamber SCM test apparatus

(From NASA Final Report: Tests of the SCM: Goembel Instruments Functional Tests)

Figure 3.1.02: Close-up of SCM test apparatus

(From NASA Final Report: Tests of the SCM: Goembel Instruments Functional Tests)

Figure 3.1.04: Apparatus used to collect scattering spectrum; "C.C." marks collision center

(From NASA Final Report: Tests of the SCM: Goembel Instruments Functional Tests)

Figure 3.2.01: SCM in place for Advance Functional Test. NASA/KSC December 2005

(From NASA Final Report: Tests of the SCM: NASA/KSC Advanced Functional Test)

Figure 3.3.02: SCM vibration test mount

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.4.01: Goembel Instruments thermal-vacuum apparatus

(From NASA Final Report: Tests of the SCM: Thermal-Vacuum Tests)

Figure A.05: Control Station

(From NASA Final Report: Appendix)

Figure A.06: The Entire Experimentation Area

(From NASA Final Report: Appendix)

24 eV electrons

(From SCM in Detail)

Peak shift analysis

(From SCM in Detail)

Figure 2.1.01: Plot from an early (1999) ion trajectory simulation of the patented SCM optics

(From NASA Final Report: Development of the SCM: Pre-Phase II Development )

Figure 2.1.02: Early drawing (circa 2000) of what would become the patented SCM electrostatic analyzer

(From NASA Final Report: Development of the SCM: Pre-Phase II Development )

Figure 2.2.09: Three board function of the SCM electronics.

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.10: Early view of SCM flight instrument design

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 2.2.11: Input/output scheme for the SCM

(From NASA Final Report: Development of the SCM: Phase II Development )

Figure 3.1.03: Electron energy spectrum of 50eV electrons scattered by Helium (collected by SCM delivered to NASA)

(From NASA Final Report: Tests of the SCM: Goembel Instruments Functional Tests)

Figure 3.3.01: Vibration test G's at varying frequencies

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.3.09: Example of the data collected during vibration tests of the SCM

(From NASA Final Report: Tests of the SCM: Vibration Tests)

Figure 3.4.03: SN001 Thermal-Vacuum test duration: six cycles between -24°C and +61°C

(From NASA Final Report: Tests of the SCM: Thermal-Vacuum Tests)

Figure 3.5.01: Data from the Non-Certified Prequalification EMI Testing of the flight prototype SCM at NASA/KSC

(From NASA Final Report: Tests of the SCM: Preliminary EMI Tests)

Figure A.03: Block diagram of the KSC SCM advanced functional test apparatus

(From NASA Final Report: Appendix)

Figure A.04: Diagram of the Electron Source Electronics

(From NASA Final Report: Appendix)

Figure A.07: Demonstration of Floating Potential

(From NASA Final Report: Appendix)

Figure A.08: Peak shapes and intensities as function of SCM floating potential

(From NASA Final Report: Appendix)

Figure A.10: 24 eV, demonstrates that beam shield allows operation up to -110 eV (the limit of the DC/DC converter)

(From NASA Final Report: Appendix)

Figure A.11: Successful testing

(From NASA Final Report: Appendix)