The Electrical Engineering Group custom designs airborne instrumentation systems to meet the requirements of the mission Project Scientist. Primary responsibilities include:

	Design of data multiplexing and data transmission systems which sample analog, digital, pulse, asynchronous, and time event Experiment and housekeeping information for transmission to ground based telemetry tracking stations for data reception, display and recording
	Design of the airborne instrumentation power, in-flight event timing, pyrotechnic and vehicle ignition, motor separation, airborne experiment and subsystem power distribution and payload ground support control systems.

The Group participates in the entire project life cycle from concept development to system design, testing, field checkout/launch support, and post flight data analysis of Airborne Instrumentation Systems. The design of an instrumentation system requires the coordination of the NSROC Mechanical, Flight Performance, Attitude Control System, Vehicle Systems engineers and project personnel. Typical design analyses include: RF link, Power Budget, RF Spectral Bandwidth, and Component Heating. The data encoding/transmission and power control system designs are used to develop wiring documentation for successful fabrication and wiring of the instrumentation and payload support systems, as shown in the photo below.

Photo Credit: Cash Payload, Mission 36.224, wiring design by EE John Gsell; wiring by ET, Dale Henderson; photo by Rob Marshall

EEG responsibilities for the development, launch and post launch phases of a sounding rocket project include the following progressive steps:

1) Initial Development
	Coordinate with the Experimenter and Experimenter's staff.
	Develop mission-specific payload control, data multiplexing, data transmission, signal conditioning, command uplink, and cabling designs that provide payload control and data multiplexing/downlinking capability.
	Generate design and fabrication documentation and present at Design Review Meeting.
	Develop system test and calibration documentation.
	Design Ground Support Equipment including umbilicals, control suitcase and programming bus.
	Test, calibrate and document the results to certify proper electrical and data encoding/data transmission operation has been achieved.
	Verify Ground Support Equipment operation and perform sequence test verification.
	Record actual system operation test results to further certify that all test results meet original mission specifications/requirements.
	Integrate the instrumentation system with the payload support subsystems to certify proper electrical/data interfacing.
	Conduct Integration Readiness Review meeting to certify that the project is ready for the Experimenter.
2) Interim Development:
	Work with the Experimenter and Experimenter's staff.
	Certify the power, signal, timing and data lines are correct.
	Mate the interfaces and power the experiments for each instrument.
	Link the telemetry RF signal data link to the telemetry ground station where the signal is received and processed to allow data signals to be fed to strip chart recorders or other display equipment.
	Display each of the Experimenter's data channels to verify proper signal response.
	Command uplink system verification.
	Connect and power all subsystems simultaneously to ensure that no RF or EM interference is experienced.
	Conduct flight simulation sequence tests to certify proper actuation of all in-flight timer-controlled functions and lift-off power back-up circuitry.
	Assemble fully certified payload for environmental testing which includes dynamic spin balance, moments of inertia, center of gravity, vibration, bend, and spin or static deployment testing.
	Conduct post vibration flight simulation sequence test to re-certify the payload integrity of in-flight event timing and power back-up functions. Should the experimenter require a calibration data tape, it is typically performed at this point in the process.
	Break payload into sections again and perform abbreviated instrumentation system checks, re-certify the altitude switch operation, and perform RF transmitter corona test in vacuum chamber.
	Document design changes, tests performed, problems encountered during testing and problem resolution for presentation at the Mission Readiness Review meeting.
3) Pre-Launch Phase:
	Pack and ship system to launch site.
	Cycle batteries and perform abbreviated instrumentation system checks.
	Re-integrate system with the payload subsystems and the Experiment(s) to certify all data and power functions are flight ready.
	Perform any necessary ground support equipment and landline modifications and tests.
	Conduct pre-flight or Range Horizontal simulation flight sequence and power back-up test.
	Assemble payload for flight; conduct payload turn-on test to certify all payload systems ready for transport to the launcher.
	Transport Payload Ground Support Equipment to the Blockhouse and configure with payload umbilicals at the launcher.
	Conduct a payload horizontal (boom test) and a payload vertical test to verify the telemetry ground station configuration and ground support equipment setup, and certify proper payload operation as well as RF signal reception, demodulation, data display, data recording and uplink command signal operation.
4) Launch Phase:
When proper science and weather conditions are met, launch the payload and monitor in-flight payload events and performance.
5) Post Launch Phase:
	Assess mission data for event timing accuracy, payload performance, and instrumentation system performance.
	Coordinate playback of requested flight data for the Experimenter's post-flight analysis.
	Generate CD-ROM of flight data for Experimenters, Flight Performance, and other mission personnel.
	Analyze housekeeping and vehicle performance information and convert data into engineering units.
	Review data for anomalous flight conditions and generate flight data graphs for the post flight report that is included in the final Mission Close-out Report.

Every facet of the electrical engineering operation is fully documented, maintained and used to provide "lessons learned" for future launches.

Example of RF Downlink Frequency Selection Verification Using Graphical Analysis of Generated RF Spectrum Plots

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Example of Instrumentation System Block Diagram

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Example of EE Interface Control Document

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Example of EE Power Systems & Budget Documentation

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Example of EE Payload Controlled Events List

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