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AGA Project
It is ADS’ main Project. Our company leADS the Working Group consisting of the following partners:
The National Institute for Aerospace Techniques Esteban Terradas (INTA) is playing a significant role in the project from September 2005, since the AGA design and development phase is being customised to build an advanced gyroscopic actuator (SAGAS-150) to be embarked as technological payload in the scientific satellite MicroSat-1, forecasted to set in orbit beginning 2010.
The purpose of this Project is to develop a new concept of gyroscopic actuator, one of the critical elements of the Attitude and Orbit Control System (AOCS) for satellites or space vehicles. The AGA is a type of Control Moment Gyro (CMG), state-of-the-art devices that provide significant torque outputs. The particular setting (patented) of the AGA gyroscopic elements, enable 2-axis control with just only one AGA device and 3-axis control with two AGA devices, providing a torque generation capacity much higher than those existing CMG in the market, and reducing –at the same time- the AGA’s mass and volume.
The following table shows AGA’s main features, compared against similar products available worlwide:
Sources:
http://astrium.eads.net
http://directory.eoportal.org/pres_PleiadesHR
ADS - own sources
The R&D project development, in parallel with the establishment of ADS, has covered two phases:
Definition Phase
Design and development phase
It is ADS’ main Project. Our company leADS the Working Group consisting of the following partners:
- Centre for Aeronautical Technologies, Basque Country (CTA).
- Engineering, Design and Analysis (IDA, SL), a mechanic engineering Company.
- Department of Missiles and Space Vehicles (MYVE), Aeronautical Engineers School – Polytechnic University at Madrid.
The National Institute for Aerospace Techniques Esteban Terradas (INTA) is playing a significant role in the project from September 2005, since the AGA design and development phase is being customised to build an advanced gyroscopic actuator (SAGAS-150) to be embarked as technological payload in the scientific satellite MicroSat-1, forecasted to set in orbit beginning 2010.
The purpose of this Project is to develop a new concept of gyroscopic actuator, one of the critical elements of the Attitude and Orbit Control System (AOCS) for satellites or space vehicles. The AGA is a type of Control Moment Gyro (CMG), state-of-the-art devices that provide significant torque outputs. The particular setting (patented) of the AGA gyroscopic elements, enable 2-axis control with just only one AGA device and 3-axis control with two AGA devices, providing a torque generation capacity much higher than those existing CMG in the market, and reducing –at the same time- the AGA’s mass and volume.
The following table shows AGA’s main features, compared against similar products available worlwide:
| PERFORMANCES | CMG 15-45S | CMG M50 | AGA-900 |
|---|---|---|---|
| Angular Momentum (Nms) | 15 | 25 a 75 | 41.63 |
| Maximum Torque Output (Nm) | 45 | 75 | 200 |
| Consumption Rate (W) | 23 | 35 | 100 |
| Mass (kg) | 15,7 | 28 | 19 |
| Signal Interfaces | MIL-STD-1553 | MIL-STD-1553 | MIL-STD-1553 |
| Manufacturer | EADS-Astrium | Honeywell | ADS |
| Control Units (3 axes) | 4 (piramid) | 4(piramid) | 3(2+1) |
| Total Mass (kg) |
84 | <100 | 47 |
Sources:
http://astrium.eads.net
http://directory.eoportal.org/pres_PleiadesHR
ADS - own sources
The R&D project development, in parallel with the establishment of ADS, has covered two phases:
Definition Phase
Design and development phase
