Dynamically Step Locked Seed Laser for Cross-Cutting SmallSat Water Vapor and Methane DIAL, Year 2

This proposal leverages recent advances in photonic integrated circuits (PIC) and microwave electronics (MWE) to develop an integrated dynamically tuned laser for a water vapor (WV) DIAL mission called out by the 2017 NASA Decadal Survey (DS). During the phase I IRAD, we developed intelligent FPGA feedforward control signals along with custom MWE to demonstrate the ability to dynamically tune a single semiconductor seed laser being developed by our SBIR partner in an effort to significantly reduce the size weight and power (SWaP) over the heritage airborne seed lasers designs to allow operation on a SmallSatellite platform. In the phase II IRAD we interfaced the drive and control electronics with the PIC being developed under a phase II SBIR and demonstrated functionality. In this proposal we look to transition the lab grade drive and control electronics to a flight design and end the project with a high TRL design that has a direct path to flight.

The proposed technology would significantly reduce SWaP (by over 10x) and complexity and enable operation on smallsat platforms. The primary-secondary mixing approach coupled with a high bandwidth PLL previously demonstrated in phase I and II IRADs will allow for continuous tuning of the seed laser frequency over the full DIAL spectrum. A feed forward current signal is used to select a new frequency set point between each shot such that the PLL can lock to the newly set wavelength. This approach allows for intelligent optimization of the transmitted wavelength on a shot to shot basis from the spacecraft to optimize the water vapor measurement as function of latitude. We have been awarded an ESTO IIP to enable space-based water vapor and methane measurements from a single ESPA class platform. The successful demonstration of this technology will enable a compact and frequency agile seed laser required to meet the stringent SWaP constraints imposed by the small sat bus. Each of the critical subsystems has been demonstrated in previous IRAD programs. The success criteria for this final program includes developing fully integrated space-hardened drive and control electronics around our seed laser PIC in a form factor consistent with operation on smallsat platforms. We will also design a conductive cooled housing that will be fabricated and tested under the IIP. We will exit the program with a fully integrated seed laser ready for environmental testing.

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