DubaiSat-2 (Arabic: دبي سات-2) is an electro-optical Earth observation satellite built by the Mohammed bin Rashid Space Centre (MBRSC) under an agreement with Satrec Initiative, a satellite manufacturing company in South Korea.[4][5][6] MBRSC's objective with DubaiSat-2 is to provide electro-optical images, that can be commercialized, for users within the United Arab Emirates and beyond and to develop and implement new technologies not used in DubaiSat-1.[7] MBRSC also intends to continue manpower training for the UAE's space program.[8] 16 UAE engineers have been working on the design, development, testing and manufacturing of the satellite. The participation of the UAE engineers, who are currently working in South Korea, has increased by 100 percent from the DubaiSat-1 project.[5][9][10]
The modules in the satellite use two CAN Bus networks to communicate with each other and it has the capacity to store approximately 17,000 km2 of image data. It also includes an experimental propulsion system for orbit correction and maintenance. The satellite's expected lifetime is at least five years.[12][13][14]
Space segment
DubaiSat-2 has a hexagonal shape. The mechanical bus consists of 2 decks and an upper sun shield to protect the cold propellants from solar and Earth radiation. The electronics are distributed on the decks and on the side panels. Four solar panels are attached to the sides of the satellite. Longerons and rails make up the bus structure frame. On the top, carbon-fiber-reinforced polymer (CFRP)struts hold the Sun shield at the baffle of the High Resolution Advanced Imaging System (HiRAIS). The High-Resolution Imaging System is attached to the bus at the internal deck. The mechanical configuration of the satellite is less than 2000 mm in height and less than 1500 mm in diameter. The total mass of the satellite is less than 300 kg.[15]
The power system supplies and controls the required voltage levels and current essential for satellite operation during its mission. The power system uses a rechargeable Li-ion battery to provide power for the satellite's payload and other subsystems. The system is divided into two stages, first is the charging stage and the second is the discharging stage. The charging stage is made of a solar power generator and power regulator. DubaiSat-2 generates more than 450W of power using four solar panels. Each solar panel contains 6 arrays and each array consists of 26 cells. The solar panels charge the batteries. The battery charging process is handled and regulated by the Battery Charging Regulators modules. DubaiSat-2 has three battery charging regulators with hot redundancy configuration which seamlessly take over if the primary battery charging regulator fails. The spacecraft can function normally with only two battery charging regulators.[15][16][17]
Mission payload
The High-Resolution Advanced Imaging System (HiRAIS) is the primary payload of Dubaisat-2. It is an advanced Earth observation Camera which captures high resolution images and is capable of other functions such as high-speed data transmission. The HiRAIS is a compact and light weight instrument; and is built from a composite material to obtain high strength while keeping its weight down. The camera is based on a Korsch optical design which uses a three-mirror configuration to reduce optical irregularities and provides a wide field of view.[18][19]
The HiRAIS consists of three main units: the Electro-Optical Subsystem, the Solid-State Recorder Unit, and the Image Transmission Unit. The Electro-Optical Subsystem is composed of the telescope, an auxiliary camera module, and a Focal Plane Assembly which are all integrated into one system. It is a pushbroom type camera with a 1-meter Ground Sampling Distance (GSD) for panchromatic imagery and 4 meter GSD in four multispectral bands.[15][16][20]
The Solid-State Recorder Unit handles the processing, storage and maintenance of image data and is capable of storing image data received from the Focal Plane Assembly during the imaging mode. It is also responsible for image data compressing, encrypting and encoding before sending it to the Image Transmission Unit during downloading mode. The unit has a storage capacity of 256 Gbit arranged in 4 identical storage boards.[15][16]
The Image Transmission Unit provides transmission of X-band data at a rate of 160 Mbit/s. It is divided into two main components: X-band Transmitter Unit and a high gain X-band Antenna.[15][16][21]
Propulsion system
DubaiSat-2 is equipped with a Hall-effect thruster. It is an electrical propulsion system with Xenon gas fuel and microwave cathode. The system will be used for the satellite's orbit correction and maintenance.[22][23]
The ground station monitors and controls the satellite. From there satellite operation planning is conducted, which includes imaging and download scenarios, mission timelines, orbit maintenance operation, and image downloads. The ground station is located at MBRSC's premises in Dubai, United Arab Emirates.[24]
Launch
DubaiSat-2 was successfully launched by a Dnepr rocket operated by Kosmotras of the Russian Federation.[25][26][27] It has been placed into a polar Sun-synchronous orbit at an altitude of 600 km and local UAE time of descending node of 10:30 am.[28][29] Initially set for the last quarter of 2012, the launch took place at 07:10:16 UTC on 21 November 2013. Thirty one other satellites were deployed by the rocket, with an additional payload remaining attached to the upper stage.[2][30][31] The revisit time for a ground location will be 8 days maximum. The tilting capability of DubaiSat-2 can go up to ±45° roll tilt, ±30° pitch tilt.
Future plans
In 2018, DubaiSat-2 and its predecessor, DubaiSat-1, was joined and will work together with UAE's third satellite, KhalifaSat.[32][33]
^"DubaiSat-2". eoportal.org. May 29, 2012. Retrieved February 5, 2023. Sun-synchronous near-circular orbit of the primary payloads (DubaiSat-2 and STSat-3), altitude = 600 km, inclination = 97.1º, LTDN (Local Time on Descending Node) = 10:30 hours. The effective revisit time of DubaiSat-2 is < 8 days for any ground location...
Launches are separated by dots ( • ), payloads by commas ( , ), multiple names for the same satellite by slashes ( / ). Crewed flights are underlined. Launch failures are marked with the † sign. Payloads deployed from other spacecraft are (enclosed in parentheses).
