Design of navigation system for the feasibility verification of a new space plane concept

Kakehashi Yuya; Takahashi Masaki

Design of navigation system for the feasibility verification of a new space plane concept

Department of System Design Engineering

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

Abstract

One of the most important issues in a design of navigation system is to estimate the system state accurately with limited sensors. This study aims at verifying the navigation system of an experimental airframe model of a new space plane concept. The most widely used algorithm to estimate the system state in the navigation system is the extended Kalman filter (EKF). However, using the EKF is not enough for the experimental airframe model to fill the required estimate accuracy. Therefore, in this study, the unscented Kalman filter (UKF) which has higher accuracy compared with the EKF is used for the state estimation of the nonlinear system. These navigation systems which use UKF or EKF are evaluated by numerical simulation.

Original language	English
Title of host publication	60th International Astronautical Congress 2009, IAC 2009
Pages	4898-4903
Number of pages	6
Publication status	Published - 2009 Dec 1
Event	60th International Astronautical Congress 2009, IAC 2009 - Daejeon, Korea, Republic of Duration: 2009 Oct 12 → 2009 Oct 16

Publication series

Name	60th International Astronautical Congress 2009, IAC 2009
Volume	6

Other

Other	60th International Astronautical Congress 2009, IAC 2009
Country/Territory	Korea, Republic of
City	Daejeon
Period	09/10/12 → 09/10/16

ASJC Scopus subject areas

Space and Planetary Science
Astronomy and Astrophysics

Cite this

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title = "Design of navigation system for the feasibility verification of a new space plane concept",

abstract = "One of the most important issues in a design of navigation system is to estimate the system state accurately with limited sensors. This study aims at verifying the navigation system of an experimental airframe model of a new space plane concept. The most widely used algorithm to estimate the system state in the navigation system is the extended Kalman filter (EKF). However, using the EKF is not enough for the experimental airframe model to fill the required estimate accuracy. Therefore, in this study, the unscented Kalman filter (UKF) which has higher accuracy compared with the EKF is used for the state estimation of the nonlinear system. These navigation systems which use UKF or EKF are evaluated by numerical simulation.",

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AB - One of the most important issues in a design of navigation system is to estimate the system state accurately with limited sensors. This study aims at verifying the navigation system of an experimental airframe model of a new space plane concept. The most widely used algorithm to estimate the system state in the navigation system is the extended Kalman filter (EKF). However, using the EKF is not enough for the experimental airframe model to fill the required estimate accuracy. Therefore, in this study, the unscented Kalman filter (UKF) which has higher accuracy compared with the EKF is used for the state estimation of the nonlinear system. These navigation systems which use UKF or EKF are evaluated by numerical simulation.

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T2 - 60th International Astronautical Congress 2009, IAC 2009

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Design of navigation system for the feasibility verification of a new space plane concept

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