kb/data/en.wikipedia.org/wiki/CCOR-2-0.md

title	chunk	source	category	tags	date_saved	instance
CCOR-2	1/1	https://en.wikipedia.org/wiki/CCOR-2	reference	science, encyclopedia	2026-05-05T09:43:00.904773+00:00	kb-cron

CCOR-2 (Compact CORonograph 2) is the second space coronograph of Compact Coronograph series and the first one in the series CCOR-1 on GOES-19. It is located aboard SOLAR-1 spacecraft (named SWFO-L1 before reaching its destination) placed at Lagrange 1 point – about 1.5 million kilometers (~930,000 miles) from the Earth towards the Sun. It will orbit the Sun at a distance between 0.974 and 1.006 AU. It was launched in September 2025 from Florida.

== Mission == CCOR-2 will provide low latency, high cadence visible light (the spectrum a human eye sees) images of solar corona and its surroundings. It will observe coronal mass ejections (CME) that are potentially dangerous to electronic infrastructure and because of that its data is going to be used for space weather forecasting. CCOR coronographs are descendants of aging SOHO/LASCO and STEREO/COR instruments. It was primarily made for National Oceanic and Atmospheric Administration and Space Weather Prediction Center.

=== Launch and destination === It was launched aboard SpaceX Falcon 9 Rocket from Kennedy Space Flight Center located on eastern Florida at 7:30 AM EDT on 24 September 2025. It has reached L1 point on 23 January 2026 – that day its first light image was taken too.

==== Forecasting ==== CCOR data (including CCOR-2) are used for space weather prediction. PyCAT (open source software designed by NOAA/SPWC and UK Met Office) and WSA-Enlil model are fed with coronograph data in order to perform calculations of CME mass, velocity and importantly – direction.

== Parameters and technical data ==

CCOR-2 was developed by US Naval Research Laboratory in Washington D.C. It has a length of about 72 centimeters (28.3 in) and due to its small size it's called Compact Coronograph. It features a 2048×1920 pixels Active Pixel Sensor detector which detects wavelengths in the range of ~450 nm to ~750 nm. The instrument has to follow several requirements, listed below.

A spatial resolution of ≤70 arcseconds Inner FOV geometric cutoff at 3.0 solar radii (

      R
      
        ⊙
      
    
  

{\displaystyle R_{\odot }}

) Outer FOV at 20

      R
      
        ⊙
      
    
  

{\displaystyle R_{\odot }}

or better A signal to noise ratio of 10 in the region between 4.4

      R
      
        ⊙
      
    
  

{\displaystyle R_{\odot }}

and 22.7

      R
      
        ⊙
      
    
  

{\displaystyle R_{\odot }}

(1.17° to 6.05°) Maximum image latency of 30 minutes CME mass estimate with an error of ≤50 per cent for CMEs with mass between

    1.0
    ×
    
      10
      
        7
      
    
  

{\displaystyle 1.0\times 10^{7}}

kg and

    5.0
    ×
    
      10
      
        14
      
    
  

{\displaystyle 5.0\times 10^{14}}

kg A closable outer door Full resolution image cadence of 15 minutes or 5 minutes for 2x2 binned images. Minimum signal intensity above noise of

    ≥
    1.0
    ×
    
      10
      
        −
        11
      
    
  

{\displaystyle \geq 1.0\times 10^{-11}}




  
    
      B
      
        ⊙
      
    
  

{\displaystyle B_{\odot }}

(

      B
      
        ⊙
      
    
  

{\displaystyle B_{\odot }}

is solar surface brightness – about -10.8 mag/arcsec²) Coronal brightness measurement with error up to 10% CME velocity estimate with biggest allowed error of 5% in the range of 200 km/s to 3400 km/s At least five years of operations with resources enough for additional five years (requirement for entire spacecraft) CCOR-2 shall be able to meet all the requirements when observing during an X50 solar flare or S4 class solar storm Observing in visible light The data must be available for SWPC reach within 30 minutes of its creation CCOR shall be capable of surviving 5 years on orbit before start of operations

==== Actual specifications ====

=== Ground Processing Algorithm === CCOR-2 images are available in FITS format, however they are also processed on the ground. The first level of the images is L0 CCSDS which is a raw readout of detector pixels. L0 CCSDS is then rotated so solar north points upwards which creates a L0B file. Level 1A image is formed by converting DN value of pixel into Mean Solar Brightness unit, division by exposure time, correcting for vignetting and detector linearity rectification. It is the main operational product used for forecasting. A median background is created from L1 by computing F-corona and stray-light based of the image. L1A with background subtraction, distortion correction application and flat field rectification creates L2 image.

== References ==