### Abstract

The optimal control problem of a spacecraft using continuous thrust where the terminal state and time interval are explicitly given is considered. We consider a new robust controller to the spacecraft rendezvous problem. Optimal rendezvous problem using continuous low-thrust is treated as optimal control problem and H_{∞} control. Using the property that both problems can be treated as two-point boundary value problem (TPVBP) of Hamiltonian system, we formulate the linear quadratic control with worst case disturbance rejection and worst case initial condition related by generating functions. Numerical simulations are given to illustrate the theory.

Original language | English |
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Title of host publication | Proceedings of SICE Annual Conference 2010, SICE 2010 - Final Program and Papers |

Publisher | Society of Instrument and Control Engineers (SICE) |

Pages | 804-810 |

Number of pages | 7 |

ISBN (Print) | 9784907764364 |

Publication status | Published - Jan 1 2010 |

### Publication series

Name | Proceedings of the SICE Annual Conference |
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### Fingerprint

### All Science Journal Classification (ASJC) codes

- Control and Systems Engineering
- Computer Science Applications
- Electrical and Electronic Engineering

### Cite this

*Proceedings of SICE Annual Conference 2010, SICE 2010 - Final Program and Papers*(pp. 804-810). [5603000] (Proceedings of the SICE Annual Conference). Society of Instrument and Control Engineers (SICE).

**Low-thrust trajectory optimization using second-order generating functions.** / Bando, Mai; Yamakawa, Hiroshi.

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

*Proceedings of SICE Annual Conference 2010, SICE 2010 - Final Program and Papers.*, 5603000, Proceedings of the SICE Annual Conference, Society of Instrument and Control Engineers (SICE), pp. 804-810.

}

TY - GEN

T1 - Low-thrust trajectory optimization using second-order generating functions

AU - Bando, Mai

AU - Yamakawa, Hiroshi

PY - 2010/1/1

Y1 - 2010/1/1

N2 - The optimal control problem of a spacecraft using continuous thrust where the terminal state and time interval are explicitly given is considered. We consider a new robust controller to the spacecraft rendezvous problem. Optimal rendezvous problem using continuous low-thrust is treated as optimal control problem and H∞ control. Using the property that both problems can be treated as two-point boundary value problem (TPVBP) of Hamiltonian system, we formulate the linear quadratic control with worst case disturbance rejection and worst case initial condition related by generating functions. Numerical simulations are given to illustrate the theory.

AB - The optimal control problem of a spacecraft using continuous thrust where the terminal state and time interval are explicitly given is considered. We consider a new robust controller to the spacecraft rendezvous problem. Optimal rendezvous problem using continuous low-thrust is treated as optimal control problem and H∞ control. Using the property that both problems can be treated as two-point boundary value problem (TPVBP) of Hamiltonian system, we formulate the linear quadratic control with worst case disturbance rejection and worst case initial condition related by generating functions. Numerical simulations are given to illustrate the theory.

UR - http://www.scopus.com/inward/record.url?scp=78649241337&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=78649241337&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:78649241337

SN - 9784907764364

T3 - Proceedings of the SICE Annual Conference

SP - 804

EP - 810

BT - Proceedings of SICE Annual Conference 2010, SICE 2010 - Final Program and Papers

PB - Society of Instrument and Control Engineers (SICE)

ER -