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Calibration/Validation Workshop 03/17 Aeolus Launch Preparations and In-flight Commissioning John Brewster - Airbus

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Aeolus Industrial Activities

2

Sine Vibration Acoustic

Launch Vehicle Separation

Thermal Vacuum Preparations Thermal Vacuum

Solar Array Integration Final System Tests

Launch campaign

Early Orbit Operations Instrument Switch on

Instrument Calibration Instrument Commissioning

Mechanical Environmental Testing

Thermal Environmental Testing

Final Assembly

Launch Campaign

Flight Operations

Now May 2017

July 2017

Transport to Launch Site

Nov 2017

Dec 2017

Mar 2018

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Aeolus undergoes Pre-launch Testing

3

Stevenage: Final integration

Toulouse: 1.Mechanical Testing 2.Post-Environmental Testing

Liege: Thermal Vacuum Testing

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Launch Campaign

4

Arrival & unpacking Fuelling Encapsulation

Integration on Launch Vehicle Final countdown & launch!

Image credit: ESA, Sentinal-2B and LPF missions

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Early Orbit Operations

5

Normal Mode: 18:00 orbit and 35 degree pitch bias to ensure optimum illumination conditions

Initial telemetry acquisition by Troll S-band Ground Station, Antarctica

Automatic Solar Array Deployment and Rotation

Orbit Repeat cycle of 111 complete orbits per week to facilitate planning by users

Separation from Vega Launcher

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6

Instrument Switch On

6

Aladin Control and Data Management (ACDM)

Transmit Laser Electronics (TLE)

Laser Heads (PLH and RLH)

Telescope

Detection Electronics Unit (DEU)

Mie and Rayleigh Spectrometers

Spacecraft Mass Memory

Science Data

1. Instrument Controller (ACDM) switch on

2. ACDM, spectrometers, and Detection Electronic Units (DEU) switch on and confirm receiver integrity by measuring noise level and sending products to Ground via Mass Memory in the On-board Computer

3. Laser Electronics (TLE) switch on and laser heads energised at low power

4. Laser heads energised at progressively higher power, echo received from atmosphere and processed by receivers. Science data sent to spacecraft mass memory for downlink to the ground.

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Instrument Calibration 1

7

Instrument Spectral Registration

Alignment of the transmitter, the Mie channel and the Rayleigh channels

Step 2 Align centre of Rayleigh Etalon to new laser frequency

Dark Current Calibration

Background noise in Imaging mode due to detector and receiver electronics

Mie Frequency Range

Mie Frequency Range

Step 1 Adjust laser frequency to maximise Mie Channel Frequency Range

Rayleigh centre

Transmit Laser UV Energy Maintenance

Perform analysis of laser energy sensitivity to control parameters (amplifier currents, temperatures) and modify parameters to maintain energy stability

Instrument Auto Test

Sweep laser frequency f0±5.5GHz and check receiver output of internal reference in Lidar mode • Verify Mie channel response • Verify Rayleigh filter shape • Verify Spectral Registration

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Instrument Calibration 2

8

Instrument Response Calibration

Detector response in Lidar mode when known wind speeds (frequencies) over dynamic range are injected

Response

(Small) Residual to Linear Fit

Instrument Defocus Calibration

Measure the diameter of the spots on the Rayleigh channel detector in order to estimate the defocus of the optical train and then to compensate it using the thermal refocusing capability of the telescope.

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Wind Speed Calibration using “Ground” Velocities

9

• Harmonic Bias Estimation (HBE) of residual ground velocities to remove biases due to misalignments and thermal effects;

• HBE process allows for multiple orbit collection to accommodate variable ground echo availability due to cloud coverage, albedo, and altitude;

• “Range Dependent Bias” compensation due to impact of variable incident angle of received signal.

• First order compensation of ground velocities along line of sight due to orbital motion and earth rotation using attitude steering law based on geolocation by spacecraft (rotation about nadir line);

• Generation of pseudo ground velocity by modified steering law enables confirmation of response slope

Orbital Time (seconds)

Apparent ground velocity (metres/sec)

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Instrument Commissioning

10

Use the HBE co-efficients in Level 1 Processing (L1P) to provide a wind speed correction for all altitudes. Using L1P, measure standard deviation

of the velocity of the ground echo and compare with predictions from mathematical model. Support ESA’s CalVal activities by

assisting the flight operations team to configure the instrument into its operating modes with the specified operating parameters Support the Handover of instrument

management to ESRIN by refinement of the weekly timeline, instrument procedures, and instrument settings Take part in In-Orbit Commissioning

Review to agree final completion of commissioning activities and beginning of Aeolus science mission.

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Summary

11

The Aeolus spacecraft system is nearing completion. Airbus has a detailed plan

for the remaining test campaigns, launch, and flight operations; Airbus is totally committed to the success of the Aeolus project and looks forward

to providing the customer and science community with the first wind measurements from the system.