Introduction for SSS project:Payload & ADCS
K.N.Toosi University of Technology
– The university was founded in 1928.
– The university was named on behalf of K.N.Toosi the famous Persian astronomer .
– It has 250 Academic staff and about 9000 students.
– There are eleven faculties, 110 research & educational labs and 5 center of excellence within the university
– The university is in top 10 universities of Iran.
– The university is collaborating with universities from Australia, Canada, Cyprus, France, Germany, Russia, and the United Kingdom.
– K.N. Toosi is one of the major R&D Partners for governmental and industrial centers in IRAN.
Faculty of Aerospace Engineering
– Faculty of Aerospace Engineering was established at 2005
– It has 14 academic staff and more than 450 students
– There are 8 educational and 6 research labs in this faculty
Space Research Lab.
Space Research Laboratory(SRL) was established in 2006 in Aerospace Engineering Faculty K.N. Toosi University of Technology.
Attitude Determination & Control System SSS-1
The APSCO Student Small Satellite (SSS) Project is proposed to develop a small satellite constellation containing 1 Microsatellite (SSS-1) and 2 CubeSats (SSS-2A/B).
The objectives of SSS project are exactly in line with the APSCO initiative that is to promote the awareness related to space science and technology among the faculty members and students from Member States universities.
This project aims to:
– Develop a three-small satellite constellation, and train students and faculties from Member States (MS) for satellite engineering through hands-on practical training until the flight model is made, and to contribute significantly for developing space education system;
– Build their own capability to develop satellites;
– Build their own payload/subsystem integrated on the satellite(s);
– Build their own capability to operate satellites and/or process image/data.
capturing low resolution images of land, water bodies, vegetation and other landscapes from Member States in order to:
– remote sensing education
– scientific research
– disaster Management
New Technology Space Flying Demonstration
-Automatic Dependent Surveillance Broadcast (ADS-B)
– Coilable Mast Mechanism
– Remote Sensing Image
– GPS/BD2 receiver
Micro Satellite SSS-1
|Category||Technical Restrictions and Constraints|
|System||Lifetime Operated in orbit ≥ 6 months On-ground storage > 1 year|
|Dimension 350mm (W)*350mm (L)*650mm (H)|
|Power >18W (Constant)|
ADCS Design and test
ADCS Design Overview
- Rate damping after the launcher separation or during operation in case of accidental increase of body rates.
- To provide a Safe Mode to ensure the survival of satellite by using only very reliable components during the contingency situation.
- To provide a simplified nadir pointing mode w/o use of the magnetic torquers for safe platform commissioning of the ADCS in orbit.
- Deploying the gravity gradient boom in order to increase stability of satellite.
- Pointing the satellite towards nadir better than 5 degree, a target on the surface of the Earth or towards some inertial target using magnetic torquers and momentum wheel.
- Pointing knowledge better than 1 degree for the target pointing mode by all the equipment.
- 1 MEMS gyroscope
- 2 Sun sensors with a common data processing unit (DPU)
- 1 Magnetometer (MGM)— measuring all 3 axes
- 1 GPS receiver
- 3 Magnetic torquers (MGT) with a common electronic unit
- 1 Reaction wheel (RW)
Attitude control unit (ACU)
- Boot mode
- Safe mode
- De-tumbling mode
- Coarse nadir pointing mode
- Coarse 3-axis nadir pointing mode
- Fine nadir pointing mode