### Abstract

Satellites orbiting the earth require large-angle and rapid rotational maneuverability. For this purpose Control Moment Gyros (CMG) needs to be applied to an attitude control actuator of a small agile satellite, because CMG can generate high torque effectively. CMG has a singularity problem which affects energy consumption and rapid actuation of CMG. In order to settle these problems we proposed feed-forward control logic using energy optimal path planning by Fourier Basis Algorithm (FBA). However, this logic does not hold robustness with several errors and disturbances. Therefore, this paper designs a feedback control system so as to obtain robustness with errors of initial CMG gimbal angles generated by natural environmental disturbances. The designed system is characterized by using the system's limit state, which is a new defined variable and is predicted by numerical integrals using nominal control inputs. The results of the several numerical simulations show the availability of the proposed logic about robustness with these errors, energy consumption, and safe use of CMG.

Original language | English |
---|---|

Title of host publication | AIAA Guidance, Navigation, and Control Conference and Exhibit |

Publication status | Published - 2009 |

Externally published | Yes |

Event | AIAA Guidance, Navigation, and Control Conference and Exhibit - Chicago, IL, United States Duration: 2009 Aug 10 → 2009 Aug 13 |

### Other

Other | AIAA Guidance, Navigation, and Control Conference and Exhibit |
---|---|

Country | United States |

City | Chicago, IL |

Period | 09/8/10 → 09/8/13 |

### Fingerprint

### ASJC Scopus subject areas

- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering

### Cite this

*AIAA Guidance, Navigation, and Control Conference and Exhibit*[2009-6205]

**Design of feedback control system using nominal inputs for satellite attitude maneuver using Control Moment Gyros.** / Kusuda, Y.; Takahashi, Masaki.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

*AIAA Guidance, Navigation, and Control Conference and Exhibit.*, 2009-6205, AIAA Guidance, Navigation, and Control Conference and Exhibit, Chicago, IL, United States, 09/8/10.

}

TY - GEN

T1 - Design of feedback control system using nominal inputs for satellite attitude maneuver using Control Moment Gyros

AU - Kusuda, Y.

AU - Takahashi, Masaki

PY - 2009

Y1 - 2009

N2 - Satellites orbiting the earth require large-angle and rapid rotational maneuverability. For this purpose Control Moment Gyros (CMG) needs to be applied to an attitude control actuator of a small agile satellite, because CMG can generate high torque effectively. CMG has a singularity problem which affects energy consumption and rapid actuation of CMG. In order to settle these problems we proposed feed-forward control logic using energy optimal path planning by Fourier Basis Algorithm (FBA). However, this logic does not hold robustness with several errors and disturbances. Therefore, this paper designs a feedback control system so as to obtain robustness with errors of initial CMG gimbal angles generated by natural environmental disturbances. The designed system is characterized by using the system's limit state, which is a new defined variable and is predicted by numerical integrals using nominal control inputs. The results of the several numerical simulations show the availability of the proposed logic about robustness with these errors, energy consumption, and safe use of CMG.

AB - Satellites orbiting the earth require large-angle and rapid rotational maneuverability. For this purpose Control Moment Gyros (CMG) needs to be applied to an attitude control actuator of a small agile satellite, because CMG can generate high torque effectively. CMG has a singularity problem which affects energy consumption and rapid actuation of CMG. In order to settle these problems we proposed feed-forward control logic using energy optimal path planning by Fourier Basis Algorithm (FBA). However, this logic does not hold robustness with several errors and disturbances. Therefore, this paper designs a feedback control system so as to obtain robustness with errors of initial CMG gimbal angles generated by natural environmental disturbances. The designed system is characterized by using the system's limit state, which is a new defined variable and is predicted by numerical integrals using nominal control inputs. The results of the several numerical simulations show the availability of the proposed logic about robustness with these errors, energy consumption, and safe use of CMG.

UR - http://www.scopus.com/inward/record.url?scp=78049287288&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=78049287288&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:78049287288

SN - 9781563479786

BT - AIAA Guidance, Navigation, and Control Conference and Exhibit

ER -