CBERS 1, 2, 2B / ZY 1A, 1B, 1B2 - Remote Sensing, Satellite Image Tutorial
CBERS 1, 2, 2B / ZY 1A, 1B, 1B2

The CBERS (China Brazil Earth Resources Satellite) or ZY 1 (Zi Yuan) satellites are designed for global coverage and include cameras to make optical observations and a data collecting system to gather data on the environment. They are unique systems due to the use of on-board sensors which combine features that are especially designed to resolve the broad range of space and time scales involved in the monitoring and preservation of the ecosystem.

The CBERS satellites will enhance and complement the existing remote sensing systems in an effort to improve our knowledge about the Earth environment and resources.

A unique characteristic of CBERS is its multi-sensor payload with different spatial resolutions and data collecting frequencies.

  • Wide Field Imager (WFI)
    The WFI has a ground swath of 890km which provides a synoptic view with spatial resolution of 260m. The Earth surface is completely covered in about 5 days in two spectral bands: 0,66mm (green) and 0,83mm (near infra-red).
  • High Resolution CCD Camera
    The CCD camera provides images of a 113km wide strip with 20m spatial resolution. Since this camera has a sideways pointing capability of 32 degrees it is capable of taking stereoscopic images of a certain region. In addition, any phenomenon detected by the WFI may be "zooned" by the oblique view of the CCD camera with a maximum time lag of 3 days. The CCD camera operates in 5 spectral bands that include a panchromatic band from 0,51 to 0,73mm. The two spectral bands of the WFI are also present in the CCD camera to allow complementing the data of the two types of remote sensing images. A complete coverage cycle of the CCD camera takes 26 days.
  • Infrared Multispectral Scanner (IR-MSS) (only in CBERS 1 and 2)
    The IR-MSS operates in 4 spectral bands such as to extend the CBERS spectral coverage up to the thermal infrared range. It images a 120km swath with a resolution of 80m (160 m in the thermal channel). In 26 days one obtains a complete Earth coverage that can be correlated with the images of the CCD camera.
  • High-Resolution Panchromatic Camera (HRC) (only in CBERS 2B)

The CBERS satellite is composed of two modules. The payload module houses the optical and electronic systems used for Earth observation and for data collecting. The service module incorporates the equipment that ensures the power supply, the control, the telecommunications and all other functions needed for the satellite operation.

The 1100W of electrical power needed to operate the on-board equipment are obtained through solar panels that are deployed when the satellite is in orbit and that are continuously oriented towards the sun by automatic control. To provide the stringent pointing accuracy needed by the sensor systems that will take high resolution images from a distance of about 800km, the satellite is equipped with a sensitive attitude control system that is complemented by a set of hydrazine thrusters which are also used in eventual satellite orbit correction maneuvers. The internal data used to monitor the satellite health are collected and processed by a distributed computer system before being transmitted to the Earth. An active and passive thermal control system provides the appropriate environment for operation of the sophisticated on-board equipment.

CBERS has a sun-synchronous orbit at an altitude of 778km, completing about 14 revolutions per day. The local solar time at the crossing of the equator is always at 10:30 A.M., thus providing the same solar ilumination conditions for comparing images taken in different days.

It takes 26 days for the satellite to revisit the same Earth location. This is the time necessary to image the entire Earth with the CCD and the IRMSS cameras that have narrow fields of view. On the other hand, using the WFI camera which is able to take images that are 900km wide, the time required for a global coverage is 5 days.

The sideways pointing capability of the high resolution CCD camera combined with the type of satellite orbit provides steroscopic vision capability for a given region with an interval of 3 days between the two elementary images.

Nation: China, Brazil
Type / Application: Earth Observation
Operator:
Contractors:
Equipment: CCD, WFI, IRMSS (#1, 2) HRC (#2B)
Configuration: Phoenix-Exe-1 bus
Propulsion: 16x1 N; 2x20 N
Power:
Lifetime: 2 years
Mass: 1450kg
Orbit: 778kmx778km,

Satellite Date LS Launch Vehicle Remarks
CBERS 1 (ZY 1A) 14.10.1999 TY CZ-4B with SACI 1
CBERS 2 (ZY 1B) 21.10.2003 TY CZ-4B with CX 1
CBERS 2B (ZY 1B2) 19.09.2007 TY CZ-4B

Source: http://space.skyrocket.de