page_title: Chasqui I
section_title: System Identification and Attitude Control – SDCA
hierarchical_section_title: Chasqui I / Project Modules / System Identification and Attitude Control – SDCA
caption_attribution_description: Español: SDCA
context_page_description: Chasqui I is a one-kilogram nanosatellite project that was launched by hand from the International Space Station during a spacewalk on August 18, 2014. The concept satellite was equipped with two cameras, a visible and an infrared, which could take photos of the Earth.
  The Chasqui I was developed by students at Peru's National University of Engineering and was part of an educational project to acquire the experience and ability in developing satellites.
  The name of the project refers to the chasqui, messengers of the Inca Empire.
context_section_description: The SDCA maintains the pico-satellite stabilization and guidance to a desired direction when necessary. Specifically, we can say that SDCA is responsible for:
  Stabilize the pico-satellite after leaving the deployer through reduction (within 0.1rad / s) and control their angular velocities.
  Maintain a pointing accuracy of 3 degrees for taking pictures of Peru and, if technically possible, having a wide coverage of South America through maneuvers of 30 degrees in roll (roll) and 30 degrees pitch (pitch).
  Maintain a less demanding pointing accuracy (e.g. 20 degrees) to enable up / down data between the pico-satellite and ground station.
  The SDCA enables the pico-satellite by using sensors to determine its attitude, calculate the correction required to achieve the desired orientation and execute the necessary maneuvers using the actuators. The attitude determination system will use magnetometers, sun sensors and attitude determination algorithms for estimating positions and angular velocities. Using GPS and gyroscopes as sensors for determining attitude will also be evaluated. The attitude control system will use electromagnetic coils and permanent magnets as actuators, forming what are known as magnetorquers. The electromagnetic coils are especially important for the stabilization of the pico-satellite once it leaves the deployer. The inclusion of the permanent magnet can have a system of active-passive control. More than one control law will be studied for possible implementation. The use of magnetic materials and hysteretic also be evaluated.
caption: System Identification and Attitude Control
exif: {}