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Preparing for a Wind Lidar Venture Class Mission. Discussion at Lidar Working Group Meeting Bar Harbor, ME August 24 – 26, 2010. Dr. Wayman Baker. Summary of Draft Statement of Work (SOW) for IDL/MDL Study of Feasibility of Deploying a DWL on the ISS. Objectives.

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Preparing for a wind lidar venture class mission

Preparing for a Wind Lidar

Venture Class Mission

Discussion at Lidar Working Group Meeting

Bar Harbor, ME

August 24 – 26, 2010

Dr. Wayman Baker


Preparing for a wind lidar venture class mission

Summary of Draft Statement of Work (SOW) for IDL/MDL Study of Feasibility of Deploying a DWL on the ISS

Objectives

  • Beginning with the NWOS design, the IDL will scale lidar

  • energy, prf, and aperture to match the ISS orbit;

  • The NASA/GSFC Mission Design Laboratory (MDL) will

  • design an updated GWOS FRAM/ELC-type payload for the ISS based on the new instrument concept, using the earlier GWOS data requirements and the ISS capabilities; The IDL/MDL will assess technology readiness, risk, and cost for an updated GWOS instrument and ISS mission;

  • The IDL/MDL will provide a preliminary determination for a

  • suitable launch vehicle. Note: The ISS Program will make the final determination.


Preparing for a wind lidar venture class mission

Summary of Draft Statement of Work (SOW) for IDL/MDL Study of Feasibility of Deploying a DWL on the ISS

Assumptions

  • A demonstration mission that will not be held to operational

  • lifetime, duty cycle and data download requirements;

  • DWL instrument based on existing GWOS and NWOS

  • concepts, both using the hybrid approach; and,

  • Pointing issues would be handled with “knowledge” rather than “control” (i.e., no gimbaling)


Preparing for a wind lidar venture class mission

Summary of Draft Statement of Work (SOW) for IDL/MDL Study of Feasibility of Deploying a DWL on the ISS

IDL SOW

  • The instrument design will meet GWOS data requirements using a hybrid DWL and the ISS 51 degree inclined orbit. It will continue taking data through the earth shadow portion of the orbit. TheIDL will:

  • Incorporate any improvements from NWOS, airborne experience, and technology advances to define an updated GWOS instrument conceptual design for the ISS;

  • Use the GWOS data requirements and ISS capabilities;

  • Use shared optics (coherent detection and direct detection lidars) with 4 azimuth angles, crossed-beam optical design, and 45 degree zenith angle as in NWOS;

  • Review NWOS trades in power, mass, volume for 100% duty cycle vs. 50%;

  • Use two-year technology projections, and provide estimates for time and cost to achieve projected technologies;

  • Notes: Would 2 telescopes save significant $ vs. 4 telescopes? With 2 telescopes, maybe the 355 could do the fore perspective and the 2053 do the aft? (MK) Use liquid laser cooling rather than further R&D on conductive cooling. (MK) How about resupplying lasers instead of laser redundancy? (DE) Could an astronaut/mission specialist make a repair? (WB)


Preparing for a wind lidar venture class mission

Summary of Draft Statement of Work (SOW) for IDL/MDL Study of Feasibility of Deploying a DWL on the ISS

IDL SOW (Cont.)

  • For the ISS environment:

    • Update GWOS instrument development and implementation cost;

    • Mass, volume, and dimensions of major components of the instrument (e.g., transceiver, optics);

    • Thermal requirements;

    • On-board computational requirements;

    • Downlink bandwidth; and, instrument vibration modes.

    • Assume a GWOS 3 year mission life, assess the redundancy of critical components with respect to mass, volume, power, and cost. Would a mission life of 3 years be a significant cost driver versus, 1 year, in terms of component redundancy, etc.?

    • Assume the NWOS concept with a reduced instrument volume using a crossed-inward optical design. Could the reduced instrument volume result in the use of a smaller launch vehicle?

    • Update and document the efficiency estimates for the laser, optics, and detectors;

    • Identify any technology or engineering “tall poles” and risks;

    • Identify any special spacecraft/instrument/ISS interface requirements from the instrument perspective; and,

    • Identify any potential instrument advantages/disadvantages from operating in one of the ISS attached modules, e.g., the pressurized Japanese Experiment Module.


Preparing for a wind lidar venture class mission

Summary of Draft Statement of Work (SOW) for IDL/MDL Study of Feasibility of Deploying a DWL on the ISS

MDL SOW

  • For the ISS environment, the MDL will design an updated GWOS mission for the

  • ISS using the earlier GWOS data requirements. The mission design will address

  • the following:

  • The operation of the instrument in the ISS environment;

  • Instrument accommodation on the ISS, including any issues related to:

  • - High frequency vibrations;

  • - Slow attitude changes, i.e., from drifts, reboosts, etc.;

  • - Available power (average and peak);

  • - Thermal management;

  • - EMI/EMC;

  • - Contamination effects such as water dumps, approaching vehicle rocket plumes, etc.;

  • - Service and component replacement on orbit;

  • - Data rates (uplink and downlink); and,

  • - Unobscurred nadir view at design nadir angle (e.g., 45 degrees).


Preparing for a wind lidar venture class mission

Summary of Draft Statement of Work (SOW) for IDL/MDL Study of Feasibility of Deploying a DWL on the ISS

MDL SOW (Cont.)

  • Ensure the following areas are in compliance with the FRAM/ELC requirements:

    • Mechanical;

    • Power;

    • Thermal;

    • Flight dynamics;

    • ISS mission operations;

    • Command and data handling;

    • Data systems;

    • Smallest launch vehicle possible, including trades against the requirements;

    • Launch;

    • Reliability; and,

    • Disposal.

  • Estimate mission cost for lifetime recommended by the IDL study;

  • Identify any unique costs related to operating in a manned environment;

  • Identify any technology or engineering “tall poles;” and,

  • Identify special spacecraft/instrument/ISS interface reqts. from a mission perspective.

  • Notes: Would data latency of 30 min be a major cost driver vs. 90 min, 150 min (WB)?

  • Don’t require quick data downlink—accept slowness of whatever link is free (M.K.&L.P.R.).

  • Don’t require vibration isolation—accept when the astronauts ruin the data (M.K.).