Flight System Implementation of the Pupil-Mapping Exoplanet Coronagraphic Observer (PECO)

Details Flight System Implementation of the Pupil-Mapping Exoplanet Coronagraphic Observer (PECO) Flight System Implementation of the Pupil-Mapping Exoplanet Coronagraphic Observer (PECO)

Jan 2009

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2009aas...21345105t&link_type=abstract

American Astronomical Society, AAS Meeting #213, #451.05; Bulletin of the American Astronomical Society, Vol. 41, p.345

Physics

Optics

Scientific paper

The 3-year Pupil Mapping Exoplanet Coronagraphic Observer (PECO) mission concept is a 1.4-m coronagraphic telescope aimed at directly imaging the habitable zones of nearby stars at optical wavelengths. PECO detects and characterizes planets down to Earth size and maps dust clouds to a fraction of our zodiacal cloud dust brightness. It uses a low CTE substrate 1.4 m diameter off-axis narrow field telescope in an Earth drift-away achieving its goals using a Phase-Induced Amplitude Apodization (PIAA) coronagraph combining high contrast, high throughput, low inner working angle and full angular resolution.
Telescope heritage is TDM and NextView. It incorporates quality optics and coatings and operates in the visible (400-900 mm) region. The secondary mirror has a linear focus actuator. The structure is thermally and vibrationally stable.
PIAA's highly aspheric optics apodize the telescope's beam without losing light. PECO also includes a high accuracy wavefront control system. Pointing is controlled at the sub-milliarcsecond level using starlight in the coronagraph. Each of the spectral channels is designed to be very compact and stable, with a small beam size to maintain high wavefront quality. The PIAA design is fine-tuned in each channel ensuring minimal inner working angle.
The SC structure is a modular design built of dimensionally stable composite material with 6 bays. We are considering the Disturbance Free Payload (DFP) which eliminates vibration coupling between the SC reaction wheels and the optical system payload. The SC pointing control system (PCS) provides 1 mas at the focal plane with a 1 Hz pointing correction bandwidth and payload provided accurate control signal from a bright star image. Propulsion employs a Spitzer-heritage redundant cold gas system using nitrogen propellant sized for 5 years.
SC I&T uses the existing LM LOTIS facility to demonstrate required light contrast under Thermal Vacuum conditions.

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