IKONOS
From Wikipedia, the free encyclopedia
 IKONOS 2 |
|
| Organization | GeoEye |
|---|---|
| Mission Type | Earth observation |
| Contractor | Lockheed Martin Space Systems |
| Satellite of | Earth |
| Launch | September 24, 1999 on an Athena 2 |
| Launch site | Vandenberg Air Force Base |
| Mission duration | 7 years |
| Mass | 726 kg (launch) |
| Webpage | spaceimaging.com/products/ikonos/ |
| Orbital elements | |
| Semimajor Axis | 7056.97 km |
| Eccentricity | 0.00013 |
| Inclination | 98.10 degrees |
| Orbital Period | 98.33 minutes |
| Right ascension of the ascending node | 68.015 degrees |
| Argument of perigee | 93.06 degrees |
| Instruments | |
| Visible cameras | 1-meter panchromatic and 4-meter multispectral |
IKONOS is a commercial earth observation satellite that collects high-resolution imagery at 1- and 4-meter resolution. It offers multispectral (MS) and panchromatic (PAN) imagery. It provides imagery beginning January 1, 2000. The company GeoEye distributes IKONOS imagery under the product name CARTERRA.
Contents |
[edit] History
IKONOS comes from the Greek word for "image". Ikonos-1 was planned for launch in 1999 but the launch failed. Ikonos-2 was planned for launch in 2000, but was renamed Ikonos and was launched on September 24, 1999 from Space Launch Complex 6 (SLC-6) at Vandenberg Air Force Base in California to replace Ikonos-1. The imaging sensors are panchromatic and multispectral. This satellite has a polar, circular, sun-synchronous 681-km orbit and both sensors have a swath width of 11 km. Its weight is 1600 pounds (720 kg). Space Imaging was acquired by ORBIMAGE to form GeoEye.
[edit] Specifications
[edit] Spacecraft
Ikonos-2 is a 3-axis stabilized spacecraft, using the LM900 satellite bus system (also referred to as Block-1). The attitude is measured by two star trackers and a sun sensor and controlled by four reaction wheels; location knowledge is provided by a GPS receiver. The design life is 7 years; S/C body size=1.83 m x 1.57 m (hexagonal configuration); S/C mass = 817 kg; power = 1.5 kW provided by 3 solar panels.
The LM900 spacecraft is a three-axis stabilized bus that is designed to carry scientific payloads in LEO orbits. It provides precision pointing on an ultra stable highly agile platform. Payloads for a variety of scientific and remote sensing applications may be accommodated including laser sensors, imagers, radar sensors, electro-optical and astronomical sensors, as well as planetary sensors. The LM900 spacecraft design was based on the CRSS imaging bus. Hardware heritage is from CRSS and IRIDIUM.
[edit] Communications
IKONOS conducts telemetry, tracking and control in the 8345.968-8346.032 MHz band (downlink) and 2025-2110 MHz band (uplink). Downlink data carrier operates in the 8025-8345 MHz band.
[edit] Spatial resolution
- 1-meter panchromatic (1-m PAN)
- 4-meter multispectral (4-m MS)
- 1-meter pan-sharpened (1-m PS)
Spectral Resolution
| Band | 1-m PAN | 4-m MS & 1-m PS |
|---|---|---|
| 1 (Blue) | 0.45-0.90 µm | 0.445-0.516 µm |
| 2 (Green) | * | 0.506-0.595 µm |
| 3 (Red) | * | 0.632-0.698 µm |
| 4 (Near IR) | * | 0.757-0.853 µm |
[edit] Temporal resolution
The revisit rate for IKONOS is 3 to 5 days off-nadir and 144 days for true-nadir.
[edit] Swath
11 km x 11 km (Single Scene)
